GB2588178A

GB2588178A - Wind energy capture apparatus, system and method

Info

Publication number: GB2588178A
Application number: GB1914752.9A
Authority: GB
Inventors: Read Roderick
Original assignee: Windswept And Interesting Ltd
Current assignee: Windswept And Interesting Ltd
Priority date: 2019-10-11
Filing date: 2019-10-11
Publication date: 2021-04-21
Anticipated expiration: 2039-10-11
Also published as: GB2588178B; GB201914752D0

Abstract

An apparatus 1 and system for harnessing wind energy comprises an energy capture device 2, a lift generation device 3, and a transmission system 10. The energy capture device may form the lift generation device. The energy capture device 2 captures kinetic energy from the wind W, and converts it into rotation of the energy capture device 2. The lift generation device 3 applies a tensile force to the energy capture device 2. The energy capture device 2 may comprise one or more rings or hoops 4 having outwardly extending wings 5. The lift generation device may be a kite 6 tethered to a ground station 7. The transmission system 10 transmits the rotation of the energy capture device 2 to a generator which converts the kinetic energy into electricity or drive. A sensor arrangement detects parameters of the apparatus, eg tension, and a control system processes and uses the parameters for the monitoring and control of the apparatus and the system. An aerial wind farm may be installed above a conventional off-shore wind farm.

Description

WIND ENERGY CAPTURE APPARATUS, SYSTEM AND METHOD

FIELD

This relates to a wind energy capture apparatus, system and method. In particular, this relates to an airborne wind energy apparatus, system and method.

BACKGROUND

The generation of electricity from renewable sources such as the wind is increasingly important in order to meet the World's growing energy requirements. In the case of wind energy, for example, perhaps the most common means of harnessing the wind to generate electricity is through the use of energy capture devices in the form of wind turbines, which generate electricity by converting kinetic energy from the wind into mechanical power in order to drive an electrical generator.

Wind turbines typically take the form of a vertical or horizontal axis rotor comprising a number of blades, which are supported at an elevated position above the ground by an upright tower. Amongst other things, the tower must be sufficiently strong and rigid to withstand the compressive forces exerted by the weight of the rotor and the bending moments exerted by the force of the wind.

An alternative method of harnessing wind energy is with the use of airborne wind energy (AWE) systems, which as the name suggests comprise an airborne structure which is attached to the ground by a tether.

In use, the airborne structure maintains the tether in tension such that, while the tether must have sufficient tensile strength, it does not require the compressive strength or rigidity of a wind turbine tower. The AWE system can thus be significantly lighter, and use less material, than a conventional wind turbine. Moreover, the use of a tether allows AWE systems to operate at significantly higher altitudes than can be achieved with conventional wind turbines. This allows AWE systems to operate in regions of typically greater wind velocity and avoid the turbulent airflows experienced near to the ground. Furthermore, the altitude of the airborne structure may be varied to suit the specific weather and wind conditions at the time of operation, thereby improving energy efficiency.

AWE systems typically generate electricity either with the use of small wind turbines mounted on a wing, or by using the lift generated by the wing itself to pay out the tether from a reel, rotation of the reel driving a generator.

US 2002/192068 describes a series of horizontal axis type rotors distributed along the upper section of an elongate torque transmitting tower/driveshaft. The tower/driveshaft projects upward at its base, supported by a cantilevered bearing means, so it is free to rotate about its own axis. The tower/driveshaft is bent downwind, until the coaxially attached horizontal axis rotors become sufficiently aligned with the wind to rotate the entire tower/driveshaft. Power is drawn from the rotating shaft at the base. Surface mount, subsurface mount, and marine installations are disclosed, including a sailboat that can sail upwind, and store energy while moored. Vertical axis rotor blades may be attached to the lower, substantially vertical section of the tower/driveshaft and even to the distal section of the tower/driveshaft, should it hang in a sufficiently vertical direction for such blades to contribute toward rotation. Vertical and horizontal axis type rotor blades may be interconnected along the entire length of the tower/driveshaft, serving as structural members, even to the point that a central shaft may be unnecessary. Blade to blade lashing may also be included. Various means, including downwind tails, lifting bodies, buoyant lifting bodies, buoyant rotor blades, and methods of influencing the tilt of the rotors, can help elevate the structure. This self-directing wind turbine, including tower, passive guidance system, multiple rotors, means for combining their rotational power and transmitting it to surface level, and load, such as a generator, can comprise as few as one single moving part.

FR3034473 describes a parachute-type kite inserted between wings, constituting the hub of a rotating kite. The conversion system causes torque and traction to interact by continuously rotating the rotary kite on its inclined plane for a combined unwinding action of winches of their respective mobile stations arranged on the rotary ring and the continuous rotation of the rotary ring on its horizontal plane and at an angular speed equal to that of the rotary kite with ring generator or winches. The peripheral conversion ropes connect the periphery of the parachute kite to the mobile stations and can be applied for the production of electricity.

However, conventional systems exhibit a number of limitations. For example, the power generated by a wind turbine, whether ground-based or in an AWE system, is proportional to the area through which the blades rotate. Accordingly, the larger the wind turbine, the greater the power generated. However, the larger the turbine, the heavier it becomes and thus the wing will require greater lift in order to be aerodynamically stable. This is typically achieved by increasing the area of the wing.

There is therefore a compromise between the size of turbines and the amount of lift required, making large scale flying wind turbines impractical.

There are also inherent safety considerations with airborne wind turbines in the event of turbine, wing or tether failures.

Furthermore, generating the power whilst airborne requires the use of power transmission between the wing and the ground, for example via an electrical cable. This can add additional weight and further inhibit the aerodynamics of the structure.

Such issues are not encountered when the lift of the wing is used to reel out a tether to drive a generator since the only airborne component is the wing, which can be made to be very lightweight since it does not need to support a turbine. Additionally, all power generation is ground based and as such no form of power transmission is required between the wing and the ground. This is therefore significantly safer than the use of airborne generators. However, after the wing has reeled out and driven the generator (traction phase), the wing will reach the end of its tether and must be reeled in using additional power input (retraction phase) and the process repeated. Operationally, this is typically achieved by performing a specific wing manoeuvre to dive the wing towards the ground, thereby reducing the tension on the tether and allowing it to be reeled in. However, this results in discontinuous power generation and periodic power usage, and requires continual active user control to reposition the wing at the end of the cycle.

SUMMARY

Aspects of the present disclosure relate to a wind energy capture apparatus, system and method and, in particular, to an airborne wind energy capture apparatus, system and method.

According to a first aspect, there is provided a wind energy capture apparatus comprising: an energy capture device configured to capture kinetic energy from the wind, wherein the energy capture device is configured to convert the kinetic energy of the wind into rotation of the energy capture device; a lift generation device configured to apply a tensile force to the energy capture device; and a transmission system configured to transmit the rotation of the energy capture device to a generator for conversion into electricity and/or drive.

As will be described further below, in particular embodiments the apparatus may comprise or take the form of an airborne wind energy capture apparatus, the apparatus configurable between a first configuration and a second, deployed, configuration in which at least part of the apparatus is deployed into the air. In particular embodiments, the energy capture device, lift generation device and at least part of the transmission system are deployed into the air when the apparatus defines the second, deployed, configuration.

In use, the wind energy capture apparatus is deployed in a region where energy from the wind is to be captured, the energy capture device being operable to capture the kinetic energy of the wind impinging on the energy capture device and convert this into rotation of the energy capture device which the transmission system in turn transmits to a generator for conversion into at least one of electricity or drive, e.g. mechanical and/or hydraulic drive. The lift generation device may be configured to move the apparatus from the first configuration to the second, deployed, configuration.

The lift generation device may be configured to thereafter maintain the apparatus in the second, deployed, configuration during operation of the apparatus.

The apparatus provides a number of significant benefits over conventional systems and techniques. For example, the apparatus is capable of harnessing the power of the wind through rotational movement of the energy capture device in a manner which permits continuous power generation through transferring torque to the generator. Amongst other things, the apparatus is portable and thus may allow for localised and/or mobile power generation, for example facilitating the capture of energy from the wind in an off-grid setting, and without the large footprint of conventional ground-based wind turbines and the like.

The apparatus further provides a stable networked configuration, where the components have wide-spaced tethering, thereby restricting deviation from the flight path, allowing for passively controlled autonomous flight.

Moreover, the lightweight and flexible nature of the apparatus means that even in the event of a failure, or breakaway, the safety risk to the surrounding environment and personnel in the area around the apparatus is reduced. The wind energy capture apparatus does not require any airborne power generating components, the apparatus harnesses the power of the wind and converts this into rotational movement of the energy capture device and transmission system. This rotational movement transfers torque to the ground for conversion into electricity and/or drive, e.g. mechanical and/or hydraulic drive, by the generator.

The apparatus may comprise a sensor arrangement configured to detect one or more parameters of the apparatus. The apparatus may comprise, may be coupled to or operatively associated with a control system. The control system may be operatively associated with the sensor arrangement. The control system may be configured to receive data output from the sensor arrangement and may be configured to control the apparatus using said data.

The control system may utilise tension and/or force in the apparatus, e.g. tension and/or force in the energy capture and/or lift generation device and/or transmission system, as a measure of power generation. For example, tension and/or force may be used as a proxy for torque and/or torque transmission, and/or torque information.

The generator may be positioned on the ground.

Alternatively or additionally, the apparatus may comprise airborne power generating components. The airborne power generating components may generate power and/or electricity which may be used to power ancillary airborne components, such as sensors, microprocessors, lights or the like. Alternatively or additionally, airborne power generating components may form the main power generating source.

Power generator and/or electricity generators may be disposed on the apparatus, for example, on a portion of the energy capture device.

Airborne power generation and/or electricity generation may be transmitted to the ground by electrical wire. The electrical wires may form or form part of a tether for the kite, for example, a reinforced electrical cable which is capable of transferring electrical power, and supporting mechanical loads applied upon the tether by the apparatus.

The energy capture device may comprise or take the form of one or more kite.

Alternatively or additionally, the energy capture device may comprise or take the form of one or more wing.

The wing may comprise or take the form of an aerofoil.

The wing may comprise or take the form of a unitary component, i.e. a single piece.

Alternatively, the wing may be formed of more than one wing sections, for example, 2, 3, 4 or more sections.

The wing sections may be connected to and/or supported by a connecting arrangement, such as a fuselage. The connecting arrangement, e.g. fuselage, may comprise sockets which may be disposed on either side of the connecting arrangement, into which the wing sections may be inserted. The sockets may be aerofoil shaped, and may be configured to match the cross-sectional profile of the wing sections.

The wing sections may be secured to the connecting arrangement using a suitable securing arrangement, such as a threaded securing means, tying and/or securing with cables or the like, or an adhesive securing means, such as glue, bond, tape, weld or the like.

The wing section lengths may be the same, or substantially the same. Alternatively or additionally, the wing section lengths may be different, i.e. may be asymmetric. For example, the ratio of lengths may be 60:40, i.e. a first section may be approximately 60% of the full length of the wing, and a second section may be approximately 40% of the full length of the wing. Alternatively or additionally, different ratios of wing section lengths may be used, for example, 50:50, where both sections are the same length, 70:30, 80:20, 90:10 or the like.

The connecting arrangement, e.g. fuselage, may provide rigidity and/or structural integrity to the wing. The connecting arrangement, e.g. fuselage, may support and/or distribute the loads exerted on the wing by the bridles.

The energy capture device may form an autogyro system. The autogyro system may generate lift through passive (i.e. non-powered) rotation of the energy capture device.

Beneficially, harnessing the power of the wind through rotational movement in an autorotation manner in this way permits continuous power generation through transferring torque to a ground-based generator or mechanical or hydraulic drive or the like. The lack of need for airborne power generation, and a direct power transmission from the airborne components to the ground, further reduces the weight of the apparatus. Moreover, such a system does not require the device to be reeled in, retracted and/or repositioned at the end of a traction phase. The autogyro system is inherently stable and can cooperate without active flight control. The autogyro system can be positioned in a region of maximum wind and the inherent stability allows the energy capture device to maintain its position, permitting continuous power generation without active control and/or implementing specific manoeuvres of the energy capture device or the apparatus as a whole.

The autogyro system rotating about an axis can allow scaling as required and multiple autogyro systems can be stacked for increased power generation and/or to compensate for variable wind speed. Stacking may comprise connecting a plurality of autogyro systems in a longitudinal direction along the axis of rotation, with each autogyro system comprising one or more kite and/or rigid wing. Alternatively or additionally, multiple autogyro systems can be stacked concentrically for increased power generation and/or to compensate for variable wind speed. For example, a plurality of autogyro devices with increasing diameters may be arranged in the same plane, i.e. one autogyro positioned radially within, or radially surrounding another autogyro. Furthermore, stacking of autogyro systems reduces the air resistance of a line, i.e. line drag, per unit area of the autogyro, thereby increasing the efficiency of transmission. Reducing line drag further increases the tension exerted on the lines, thereby reducing their flex, and increasing their ability to transfer torque.

The autogyros may also be stacked to suit particular geometrical conditions, for example, aspect ratio of the apparatus. For a given autogyro diameter, an optimal stack height can be set to ensure a particular aspect ratio and stack stability.

Alternatively or additionally, autogyros may be configured to be entirely separate from other autogyros, e.g. connected separately, thereby ensuring an entirely separate system. This allows the different autogyros to be operated at different rotational speeds without affecting other autogyros and/or without becoming tangled or connected to other autogyros, components or lines or the like.

This permits further stacking of multiple planes or layers of concentrically stacked autogyros, i.e. an apparatus may comprise a plurality of layers of autogyros positioned on different planes along the longitudinal direction along the axis of rotation, with each of the planes or layers comprising a plurality of concentric autogyros extending radially outwardly from the axis of rotation. By such provision, an apparatus may comprise any number of autogyros to suit specific wind, climatic, power generation, airspace, size limitations or the like.

In a stack of a plurality of autogyros, the formation of each autogyro may be varied and/or may be different from other autogyros.

For example, the lowermost autogyros and/or energy capture devices and/or kite and/or wings, i.e. those closest to the ground, may be configured to have a greater bank angle than the higher autogyros and/or energy capture devices and/or kite and/or wings, i.e. those closer to the lift device and further away from the ground. By such provision, those with a greater bank angle (the lower autogyros and/or energy capture devices and/or kite and/or wings) may generate a greater radially outwardly acting force, i.e. an inflation force, during rotation. A greater inflation force may allow more torque to be transmitted from the higher autogyros and/or energy capture devices without crushing, deforming, twisting or otherwise affecting the autogyros and/or lines and/or other non-rigid components.

Each autogyro configuration may have optimal flight characteristics, which may balance the ability to transmit torque (e.g. the inflation force) and the compressive, crushing forces exerted on the autogyro by the torque of the apparatus.

Additionally or alternatively, the apparatus may be configured to operate in a reciprocal linear motion. The autogyro may be connected to a reel by a tether. The lift of the autogyro may be used to pay out the tether from the reel, driving rotation of a generator. Once the tether is fully extended, the autogyro may be configured to spill power, i.e. lose some or all lift and/or thrust, allowing the autogyro to lower or be lowered to the ground. The autogyro may lower to the ground in a passive manner, i.e. without active control, alternatively, a specific control manoeuvre may be performed to lower the autogyro to the ground. Once the tension on the tether has been removed, the reel may then be reeled in, for example, while the autogyro is falling towards the ground and/or once the autogyro has fallen to the ground, thereby reducing the length of the tether and returning to a first position. The process may then be repeated. In this way, the autogyro may act in a reciprocal, yo-yo manner. By such provision, this configuration may be similar to that of the conventional AWE systems described above.

The autogyro may be supported by, and/or may travel along the lift generation device, i.e. the range of motion may be limited to a specific track along the lift generation device. Alternatively, the autogyro may not be supported any may free to move in any direction, i.e. in free space.

The apparatus may be capable of both of rotational motion and reciprocal linear motion. The range of motion of the apparatus may be varied whilst airborne. For example, the apparatus may alternate between generating power in a rotary manner according to the first aspect, and generating power in a reciprocal linear motion as described above. The reciprocal linear motion may be implemented in certain conditions, for example, to generate a pulse in power generation, for example, to meet sudden increase in power demand.

Alternatively or additionally, the apparatus may be capable of both rotational motion and reciprocal linear motion simultaneously, i.e. the autogyro may act in a reciprocal linear motion, whilst also rotating.

The energy capture device may comprise a ring, herein referred to as an active power ring. The active power ring may be circular, or substantially circular. Alternatively or additionally, the active power ring may be polygonal shaped, for example, pentagonal, hexagonal, heptagonal, octagonal or the like.

A plurality of active power rings may be arranged in a layer. The layer may comprise a plurality of active power rings arranged concentrically.

A plurality of active power rings of differing diameters may be arranged in a concentric arrangement, i.e. one disposed radially inwardly or outwardly from another.

A plurality of active power rings may be arranged in a coplanar arrangement, i.e. disposed on the same plane.

Alternatively or additionally, the position of at least one of the concentrically arranged active power rings within a layer may be different relative to the others, for example, at least one active power ring may be raised, lowered, angled, tilted or the like relative to an adjacent concentric active power ring. The relative positions of the active power rings may allow characteristics and/or properties of the layer to be varied, for example, the angle of attack (AoA), bank angle, the radius of rotation, yaw angle, speed of rotation, speed of translational movement in a wind window, lift, propulsion, kite and/or wing bow angle, or the like.

The apparatus may comprise a plurality of layers, for example, 2, 3, 4, 5, 6, 7, 8 or more layers.

The plurality of layers may be disposed longitudinally along the axis of rotation of the apparatus The layer may comprise a plurality of active power rings, for example, 2, 3, 4, 5, 6, 7, 8 or more active power rings.

The active power rings may comprise a plurality of kites and/or wings, for example, 2, 3, 4, 5, 6, 7, 8, or more kite and/or wings.

The ground based area occupied by the apparatus may be constant while increasing the longitudinal length, and/or number of kites and/or wings of the apparatus.

The ground based area occupied by the apparatus may be constant while increasing the power output of the apparatus.

The stackable nature of the autogyro systems provides the ability to scale the wind energy capture apparatus to suit specific power requirements and/or current wind or climatic conditions. The rotational nature of the apparatus means that increasing the number of stacks of autogyro systems, and thus the effective power output, only increases the length of the apparatus along the axis of rotation, and does not affect the cross sectional area, or ground-based area of the apparatus. Thus, there are minimal consequences of increasing the scale of the apparatus, other than the increased number of kites and lines required, and subsequent increase in weight. However, the components are exceedingly light, with conventional kite lines being manufactured from Dyneema®, which typically weighs 1-2 grams per metre, and conventional kite wings being manufactured from ripstop nylon, which typically weighs 30-50 grams per square metre. Consequently, the increase in weight when stacking multiple autogyro systems is minimal in relation to the increase in power generation. The only theoretical limit to the amount of autogyro systems that could be stacked is the breaking load of the lines, which, for a single Dyneema 8 line of 2mm diameter is typically between 300kg and 500kg. Thus, with multiple lines and/or larger diameter lines, the breaking load could potentially be significantly higher. This all means that increasing the scale of the apparatus in achievable with minimal consequences Advantageously, arrays of small scale kites and/or wings in this way permit extensive scaling. Small wings, which may be banked, angled, or tilted, disposed on an hollow axis autogyro behave differently to more conventional horizontal axis type turbines, in particular, the aerodynamic forces experienced by the small banked wings, actively expand the autogyro whilst rotating. This greatly increases the amount of torque which can be transmitted through the apparatus. The proposed system may operate purely in tension, e.g. using tensile line and tensile kite and/or wing elements.

The proposed system may not experience any compressive forces, thereby obviating the need for rigid components to support compressive forces. The expansion of the ring of kites can be further enhanced with fairings fitted to the autogyro and/or lines and/or radially aligned kite and/or wing elements, thereby further increasing the radial outward force exerted by the kite and/or wings.

The plurality of autogyro systems may be interconnected by at least one connecting line, cord, cable, rope or the like.

The use of multiple lines establishes a degree of redundancy in the apparatus since if a single line breaks, the applied loads may carried by other lines, and the system may remain structurally and aerodynamically stable, allowing the apparatus to continue to operate safely without breaking away. The apparatus may be designed to continue to operate safely with a reduced number of lines. This allows the device to be safely lowered to the ground for repair or replacement of the broken component.

Alternatively, the apparatus may be configured to automatically fall gently to the ground once a single line breaks. This makes such systems significantly safer than systems which use a single wing, and/or a single tether or point of contact.

Alternatively, repair may be performed in an aerial position, i.e. when the apparatus is in use, by an additional aerial device, for example, a drone, or telescopic apparatus, aerial work platform, cherry picker device or the like.

The energy capture device may be cylindrical or generally cylindrical.

Alternatively the energy capture device may be conical or frusto-conical.

The energy capture device may have a central axis.

The energy capture device may be configured to turn and/or rotate in a particular direction, and/or rotate about the central axis of the energy capture device.

The energy capture device may comprise one or more kite and/or wing. The kite and/or wing may comprise, be, or form a soft, i.e. non-rigid, fabric kite. The kite and/or wing may be in the form of a ram air kite, a foil kite, leading edge inflatable (LEI) kite, box kite, rigid frame kite, fixed wing structure or the like.

Alternatively or additionally, the kite and/or wing may comprise, be, or form a rigid aerofoil, propeller, blade or the like.

The kite and/or wing of the autogyro may be manoeuvrable relative to the energy capture device and/or active power ring and/or may be powered. Alternatively, the kite and/or wing may be fixedly attached to the energy capture device and/or active power ring, i.e. stationary relative to the energy capture device and/or active power ring.

The one or more kites may comprise, be, or be formed of a lightweight, strong material, such as a woven fabric such as ripstop nylon or the like.

The one or more wing may comprise, be, or be formed or a lightweight, strong and rigid material, such as carbon fibre, plastic, composite, metal, or alloy or the like.

The one or more kites may comprise a rigid frame.

The one or more kites and/or wings may be interconnected, and/or may be tethered to the ground using a high strength, low weight lines, such as Dyneema® lines.

A rigid aerofoil, propeller, blade or the like may provide high power to weight and fast rotation in small sizes, when compared to soft, non-rigid kites which may provide high power to weight with slower rotation in large wing sizes. Soft, non-rigid kites may provide improved crash handling characteristics, for example, the soft, nonrigid material, e.g. fabric, may be less likely to fracture, and/or cause damage to itself or other bodies in the event of a collision when compared to rigid aerofoils, propellers, blades or the like which may be more likely to fracture, and/or cause damage to itself and other bodies in the event of a collision The kite and/or wing may be asymmetric about at least one axis, e.g. may be curved, tilted, twisted or the like. By such provision, the kite and/or wing may be shaped and/or profiled for improved rotational performance, e.g. may be shaped to turn in one direction only, and/or be shaped to turn in one direction more readily than another direction. For example, the kite and/or wing may comprise swept, banked, twisted edges and/or faces and/or formations. Alternatively, the kite and/or wing may be symmetric about at least one axis.

The energy capture device and the lift generation device may be separate. By such provision, the lift and thrust force components of the device may be separable. Alternatively, the energy capture device and the lift device may be the same device.

The energy capture device may comprise at least one rotor element. The rotor element may comprise an active power ring. Additionally, the energy capture device may comprise a passive power ring. The kite and/or wing may be connected to the active power ring, for example, may be disposed circumferentially on the rotor element. The rotor element may be in the form of a hoop which may be circular, or substantially circular, and may have a central axis. The hoop may be formed, made, constructed of metal, plastic, composite materials or the like.

The hoop, and/or active power ring and/or passive power ring may be in the form of a circular and/or annular aerofoil, i.e. a generally conical or frusto-conical shape. By such provision, the hoop, and/or active power ring and/or passive power ring may provide lift and/or thrust, and/or may channel, funnel or redirect the airflow passing over the energy capture device, e.g. for improve aerodynamics.

The energy capture device may be connected to the ground station using a suitable high strength, low weight connecting means such as, ropes, tether, cables, lines, cord, Dyneema® rope or the like. Said means may connect the energy capture device to the generator and/or may drive the generator. These lines are hereinafter referred to as driver lines.

The active power ring may connect to the connecting arrangement, e.g. the fuselage.

The active power ring may comprise an attachment arrangement for attachment to the connecting arrangement, e.g. the fuselage.

The kite and/or wing may be connected to the driver lines via a bridle. The bridle may comprise a plurality of lines or strings connecting the kite and/or wing to the driver line.

The bridle may be formed of a suitable high strength, low weight connecting means such as, ropes, tether, cables, lines, cord, Dyneema® rope or the like.

The bridle may comprise at least 2 lines, or at least 3 lines, or at least 4 lines, or at least 5 lines, or at least 6 lines.

The bridle may maintain the kite and/or wing at a certain shape, angle, flying position, angle of attack (AoA), bank angle, or the like.

Alternatively, or additionally, the kite and/or wing may comprise one or more supporting member and/or reinforcing member and/or rigid structure. The kite and/or wing may comprise a supporting member which may be located, disposed, or attached to the leading edge of the kite and/or wing. Alternatively or additionally, supporting members may be located, disposed or attached to the wing tips, and/or trailing edge, or may be disposed on all edges of the kite and/or wing, thereby creating a rigid frame for the kite and/or wing.

The one or more supporting member may obviate the need for bridles to connect the kite and/or wing to the active power ring, energy capture device or driver lines.

The bridles may be configured to connect to the connecting arrangement. Alternatively or additionally, the bridles may connect to the wing sections, and/or wing tips.

The active power ring may connect to the connecting arrangement, e.g. the fuselage, via the bridles.

The connecting arrangement, e.g. fuselage, may comprise an attachment means for attachment to the active power ring.

The connecting arrangement, e.g. fuselage, may connect to the active power ring. Alternatively, the connecting arrangement may connect to the active power ring via the bridles.

The kite and/or wing may comprise a load spreader which may take the form of a rigid bar or beam, which may be configured to balance and/or distribute the loads over the area of the kite and/or wing. The bridles may connect to the load spreader. Alternatively or additionally, the fuselage may act as a load spreader.

In an embodiment in which a plurality of rotor elements are employed, the rotor elements may be arranged in series, and may be aligned axially along the axis of rotation. The plurality of rotor elements may be combined into a stack. The plurality of rotor elements may be connected together via the driver lines.

The at least one kite and/or wing may be configured to provide power and/or propulsion in a particular direction, e.g. a direction tangential to the rotor element. By such provision, the kite and/or wing may cause the rotor element to rotate about the central axis. The rotor element may form a hollow axis kite turbine.

The rotor element may transfer rotational energy to the driver line. The rotor element may generate a torque by capturing at least a portion of the energy of the wind and converting it into rotational motion, i.e. the rotor element and attached kite and/or wing may allow the linear wind velocity vector to be at least partially converted into rotational velocity of the energy capture device.

The energy capture device may be connected to the ground station via the driver lines. By such provision, a rotational movement and/or torque may be transferred from the energy capture device to the ground station.

The diameter of the rotor element may be variable, alternatively or additionally, the rotor element may be interchanged for ones of different diameters. By such provision, the radius of rotation of the device may be variable and/or the capture area of the kite and/or wings may be varied, e.g. increased or reduced, and/or torque generation may be varied, e.g. increased and/or reduced. The ability to maximise the radius of rotation may limit, reduce the centrifugal acceleration and may reduce or obviate the risk and/or dangers of an over-speed condition, in which the device may rotate at an uncontrollable rotational velocity. Furthermore, the lightweight tensile nature of the rotor element may also obviate the risk of an over-speed condition, i.e. rotating uncontrollably quickly.

The orientation of the kite and/or wing, e.g. angle in yaw, pitch, roll orientations, may be variable. The tension on the bridle may be variable. By such provision, parameters of the kite and/or wing, e.g. the angle of attack (AoA), bank angle, the radius of rotation, yaw angle, speed of rotation, speed of translational movement in a wind window, lift, propulsion, kite and/or wing bow angle, or the like may be variable.

By such provision, the velocity of the kite and/or wing, and thus the rotational velocity of the rotor element may be increased or reduced, and/or the amount of lift and/or thrust and/or drag may be varied. By such provision, safe operation of the energy capture device can be ensured over a wide range of conditions, and/or may allow the energy capture device to handle turbulence, sudden changes or surges in wind velocity and/or power, i.e. wind gusts.

The wind energy capture apparatus may be manoeuvrable and/or repositionable within the wind window. The wind window being the three-dimensional region downwind of an anchor point of an aerial wind powered device, e.g. a kite. The wind window may comprise a power zone in which the force exerted by the wind powered device is greatest, and a neutral zone, in which the force exerted by the wind powered device is minimal or negligible. The neutral zone is typically referred to as being at the edge of a wind window.

The wind energy capture apparatus may be angled and/or variably angled within the wind window. By such provision, the apparatus may adapt to varying wind conditions and direction. The apparatus may be passively repositionable i.e. self-moving in the wind, or actively controlled or repositioned in the wind window.

The rotor elements, kite and/or wings may comprise through-wing tethers and bridles which may be linked in order to transmit signals, tension, power or signals. A plurality of kites and/or wings may be stacked. A stack of kites and/or wings may be manoeuvred, steered, depowered or landed as a single unit.

The energy capture device and/or kites and/or wings may have on-board winders which may be sprung or driven by a controlled or passive power source, which may allow adjustment of the bridles or tethers, and relative positions of adjacent kites and/or wings, radius of rotation of the kite and/or wing, relative positions of power rings or the like. The kites and/or wings may comprise pulleys which may be configured to reel in, or accept slack bridling and/or tethering, which may allow adjustment of the bridles or tethers, and relative positions of adjacent kites and/or wings, radius of rotation of the kite and/or wing, relative positions of power rings or the like.

The energy capture device and/or kites and/or wings may comprise a turbine, which may be disposed on a surface of the kite and/or wings. The turbine may be capable of generating power which may be used for on-board control, for example, powering sensors, motors, winches or the like, or for otherwise controlling the kite and/or wing, and/or for exporting/transferring power to the rest of the apparatus for control of other components of the apparatus, and/or for power and/or electrical generation.

As described above, the lift generation device is configured to apply a tensile force on the energy capture device and/or the apparatus. By such provision, the apparatus and/or energy capture device may maintain a rigid or substantially rigid shape when the apparatus defines the second, deployed, configuration.

The device may comprise a tensioning arrangement, which may support the device and/or may apply a tensile force between the tensioning arrangement and the ground station.

The tensioning arrangement may comprise a kite in the form of a lift and/or launch kite.

The lift and/or launch kite may be used to launch the apparatus.

The lift and/or launch kite may be in the form of a ram air kite, a foil kite, leading edge inflatable (LEI) kite, box kite, rigid frame kite, fixed wing structure or the like. The lift and/or launch kite may be in the form of a fractal arch or mothra type kites comprising individual interconnected kites in a larger load-path across the span of a generally arched structure, cellular structure kites and/or large scale rotatable tensile lifting surfaces with annular perimeter rope rails. The lift kite may be in the form of a high drag, semi rigid structure, for which a small kite turbine is able to generate power from a position low in the wind window by sweeping across the wind window, for example, in the maximum power zone of the wind window.

The lift generation device may comprise a lattice structure, e.g. a diamond lattice structure, in which all interconnecting lines are in tension and/or all forces exerted on, or experienced by the lines are equalised. The lattice structure lift generation device may comprise a plurality of lift generation devices which may be positioned on a plurality of lift planes positioned along the axis of rotation. Multiple layers of lift generation devices may provide steadier and/or stronger lift forces when compared to a single layer of lift generation devices.

The lift generation device may comprise tethering which may pass through a portion of the lift generation device, such that a plurality of lift generation devices may be arranged in a stacked configuration. Advantageously, fractal layers of lift kites may be isotropic with regard to oncoming wind whilst using the stabilising effects of wide anchored network kites.

The lift kites may be mounted by their wing tips on a circular rope rail line disposed inside hexagonal cells. Advantageously, tightly connecting hexagonal cells with a circular rope creates a rail on which components may move freely whilst still being supported. The lines of the lift kites may be provided with or without ancillary mounting pads, patches, webs or other connectors for extra lifted line utility devices.

The lift kites may comprise a controller which may permit tension sensing, local wind generation, power transmitted along the lift line, communication and power for parachute landing.

A number of kites and/or wings may be dependent on the lift kite, for example, connected to and/or driven by the lift kite.

The position and/or tension of the lift kite may be varied, e.g. the lift kite may be steered, to affect the performance, angle of attack, alignment to the wind or the like, of the apparatus and/or a set of kites and/or wings dependent on the lift kite.

Alternatively or additionally, the tensioning arrangement may be supported by a building or structure to which the device may be attached and/or secured. The tensioning arrangement may be, form or comprise the lift generation device, or may comprise the lift component of a force imparted on the device.

In use, the lift and/or launch kite may be launched, and whilst airborne, may provide support for the energy capture device. The tensioning arrangement may be connected to the kite using a suitable high strength, low weight connecting means such as, ropes, cables, lines, cord, Dyneema® rope or the like. This line is hereinafter referred to as a lift line.

The rotor element and/or autogyro may be supported by the lift line.

The rotor element and/or autogyro may rotate about the lift line.

One or more bearings or similar friction reducing device may be disposed between the rotor element and/or autogyro and the lift line. By such provision, the lift line may support the rotor element and/or autogyro whilst minimising or at least reducing friction.

The lift line may support one or multiple rotor elements and/or active power rings and/or autogyros.

The bearing may be annular in shape. The bearing may be disposed on the lift line, i.e. the lift line may be threaded or inserted through the central orifice of the annulus of the bearing.

The active power ring may comprise a bearing or other suitable friction reducing device.

The passive power ring may comprise a bearing or other suitable friction reducing device.

The active power ring may be connected to the bearing or other suitable friction reducing device, and may be connected via one or more spoke and/or tensile spoke line. The one or more spoke and/or tensile spoke line may be radially attached, connected or disposed on the active power ring. Alternatively, the one or more spoke and/or tensile spoke line may be attached, connected or disposed on another part of the rotor element or energy capture device, e.g. to the kite and/or wing.

Each active power ring and/or passive power ring may comprise a bearing or other suitable friction reducing device. Alternatively, only a single active power ring, for example, the uppermost active power ring, i.e. the active power ring closest to the lift device, may comprise a bearing or other suitable friction reducing device. By such provision, all other active power rings and/or passive power rings disposed below the uppermost active power ring, i.e. closer to the ground station, may connect directly to the uppermost active power ring, obviating the need for each active power ring and/or passive power ring to comprise a bearing or other suitable friction reducing device.

The position and relative positions of the rotor element may be variable along the lift line, i.e. can be moved in and/or out along the line, and movement may be performed while the device is in use, i.e. when live.

The rotor element may be moved along the lift line by means of winching or other mechanical arrangement.

The rotor element may be moved along the lift line by means of its own lift and/or thrust, for example lift and/or thrust generated by the kite and/or wing.

The rotor element may be free, i.e. not restrained, to passively move and/or lift relative to the lift line.

The apparatus may comprise a safety line which may be connected to the apparatus. The safety line may comprise, be, or form a suitable high strength, low weight connecting means such as, ropes, cables, lines, cord, Dyneema® rope or the like. The safety line is herein referred to as the backline.

A first end of the backline may attach to the lift line.

The backline may attach to the lift line at a location between the uppermost energy capture device and/or autogyro, i.e. the energy capture device and/or autogyro farthest away from the ground, and the lift device.

The backline may attach to a bearing.

The position of attachment of the backline on the apparatus may be variable and/or adjustable. For example, the attachment point of the backline may be adjusted to account for different conditions.

A second end of the backline may attach to the ground station and/or anchor.

Alternatively or additionally, the backline may be connected or attached to a separate anchor, herein referred to as the backline anchor.

The backline anchor may be repositionable.

The backline anchor may be positioned so as to be downwind of the ground station and/or generator. Alternatively or additionally, the backline anchor may be positioned so as to be upwind of the ground station and/or generator. Alternatively or additionally, the backline anchor may be positioned level with the ground station and/or generator.

The backline anchor may provide a secondary anchor for the apparatus, which may provide a backup anchor in the event of a breakaway of the apparatus and/or a component of the apparatus.

The backline may be configured to be elastic, i.e. made from an elastic material and/or may be variable in length.

The backline may be configured to be in tension.

Alternatively, the backline may be configured to be slack, i.e. not taut, by ensuring that the length of the backline is longer than the length of the driver line and/or lift line between the anchor and the backline attachment point. By such provision the backline will not affect operation of the apparatus. In the event of a breakaway, the apparatus, or a component of the apparatus may break away and travel downwind from the anchor, at the point when the distance between the anchor and the broken away components becomes equal to the length of the backline, the backline will become taut and retain the broken away components and prevent them from travelling further downwind.

The backline may provide a suitable safety device to restrain the apparatus in the event that the apparatus or component of the apparatus breaks away from the ground station and/or anchor and/or apparatus.

The backline may be used to launch the apparatus, The backline may be used to aid launching of the apparatus, The backline may be used for recovery of the apparatus, or component of the apparatus.

The backline may act as a tether.

The backline may be used to modify the form of the apparatus, a kite and/or wing, autogyro, energy capture device, or the like, thereby affecting the angle of attack, bank angle, generated lift, generated thrust, generated propulsion or the like. The backline may be used to deliberately stall the apparatus and/or the autogyro and/or the energy capture device and/or lift device.

The backline may improve safety of launching and/or operation and/or landing of the apparatus.

Alternatively, the launch kite, and/or device may be launched and/or landed and/or captured and/or recovered with the use of one or more aerial drones. For instance, one or more drone may be used to perform one or more of; shroud a choke net over a lift kite, collapse a lift kite into forward stall; remove or install individual lifter kites; add the interconnecting hex top mesh link lines over wide distances to avoid having to handle the line over the ground at launch. Alternatively, or additionally, the one or more aerial drones may perform repair and/or replacement of components of the apparatus, which may be performed whilst airborne.

Alternatively or additionally, one or more aerial drone may be used for steering and/or manipulating the apparatus or components of the apparatus, for example, the lift kite and/or the energy capture device and/or driver lines or the like.

One or more aerial drone may be used to attach lines to the bridles of the kite and/or wing and/or the lift kite.

One or more aerial drone may be used to control the lift kite by means of remote tensioning of the lines, for example the bridles and/or driver lines and/or lift line and/or lines used for steering a kite and/or wing and/or apparatus or the like.

The one or more aerial drone may be used to attach or connect tensioning lines to the apparatus. The tensioning lines may be used to assist tensioning of the apparatus and/or lines of the apparatus.

The lift kite may be static, i.e. static within the wind window. Alternatively or additionally, the lift kite may be non-static, i.e. may move, translate, rotate, sweep or the like, within the wind window, and/or may travel traverse to the wind direction, e.g. the lift kite may be a crosswind kite.

The lift kite may be controllable and may be repositioned whilst in use, e.g. while live. For example, the lift kite may be moved between a static position, to a non-static position during use, depending on the lift required in the system, required power generation, power take-off (PTO), or external conditions, e.g. wind or climate.

The thrust component of the apparatus and the lift component of the apparatus may be separate, i.e. a separate energy capture device and lift device. Alternatively, the thrust component of the apparatus and the lift component of the apparatus may be integral or unitary, i.e. the energy capture device may be the lift device.

The energy capture device may provide lift to the apparatus, e.g. the energy capture device, e.g. autogyro, may form the lift generation device.

The energy capture device may supplement the lift generated by the lift device.

Alternatively, the energy capture device may provide 100% of the lift of the apparatus. In such an embodiment, the lift line and lift kite are not necessary and may be removed. In an embodiment in which the lift line and lift kite are not present and 100% of the lift is provided by the energy capture device, the tension of the system may be transferred through the driver lines.

The energy capture device, e.g. the autogyro, may be used to launch the apparatus. For example, the kite and/or wing of the autogyro may be manoeuvred, moved or repositioned in order to provide lift, i.e. the lift provided by the energy capture device may be varied, for example, between zero lift, and maximum lift. The angle of attack may be varied and/or the kite and/or wing may be moved relative to the oncoming wind to a position where the wind acting upon the kite and/wing provide sufficient lift to launch the autogyro and/or the apparatus.

Alternatively or additionally, the apparatus may be operable in reverse in order to launch the apparatus. For example, the generator may be actively driven, for example by a motor, thereby inducing rotation of the autogyro and generating lift on the autogyro surfaces. Once airborne, the motor may be switched off, and the autogyro may be used to generate power.

The generator may form or form part of the motor, which may be used to generate power, or to drive the apparatus. The generator may alternate between generating power, and driving the apparatus whilst the apparatus is in use, i.e. while airborne. For example, the generator may be driven during use of the apparatus, for example, to compensate for a sudden drop in wind speed, to twist or untwist and/or prevent twist of the apparatus, autogyros, driver lines or the like.

Driving the apparatus in this manner allows the apparatus, e.g. the autogyro and/or energy capture device, to be used as a stacked set of propellers, which may be used to generate a thrust force.

The apparatus may be connected to a mobile device, for example, the ground station and/or anchor may be connected to a mobile device. By such provision, the thrust generated by a driven apparatus may provide a thrust to the mobile device, thereby causing propulsion and/or movement of the mobile device.

Therefore in the case the motor/generator is mounted on a mobile device, when the autogyro and/or the energy capture device is driven to rotate, propulsive forces may be induced on the mobile device in order to propel the mobile device toward the direction of the propulsive force. Realigning the autogyro and/or the energy capture device may change the propulsive force and may allow the mobile device to be steered and/or the propulsive force to be increased or decreased. In this way the turbine may also be used as a device to enable propulsion of a mobile device.

The mobile device may comprise a wheeled, tracked, sledded vehicle or the like, suitable for use on land such as a car, sled, or the like. The mobile device may comprise a water craft, for example, a boat, raft or the like. The mobile device may comprise an airborne craft, for example, an airship, blimp or the like.

Alternatively, other powered means may be used to launch and/or lift the apparatus, for example, an aerial drone, fan or air blower or the like.

The driver lines may be oriented parallel each other. The driver lines may be disposed circumferentially around the power rings. Alternatively or additionally, in an embodiment in which the power rings are polygonal, the driver lines may be disposed on an outer edge of the polygon. Alternatively, or additionally, the driver lines may be oriented at an angle to the power rings, for example, oblique to the power ring. The driver lines may be configured in a helical arrangement, for example, a helix, double helix, triple helix or the like.

In use, the driver lines may become twisted, i.e. the driver lines may be reconfigured from a parallel arrangement to a helical arrangement.

In use, the driver lines may become untwisted, i.e. the driver lines may be reconfigured from a helical arrangement to a parallel arrangement.

As described above, the kite and/or wing may cause the capture device to rotate about the lift line.

The rings may be connected by non-rigid lines.

A driven ring, i.e. an active power ring, may be forced to rotate faster than an adjacent ring. For example, an active power ring disposed at the uppermost end of the apparatus when in use, i.e. closest to the lift device, may be caused to rotate, where as an active power ring, and/or a passive power ring disposed lower on the apparatus, i.e. closer to the ground station, may rotate slower and/or may not be powered.

Consequently, the lower rings may be driven, i.e. forced to rotate by the upper most active power ring. Since the rings are connected by non-rigid lines, the lines may move relative to the rings before the tension in the lines is sufficient for the lines to drive the lower rings. This may therefore introduce a delay or time lag in rotation between the uppermost rings and lower rings.

Alternatively or additionally, different rings may rotate at different speeds, for example, a ring may rotate faster than another ring due to a difference in wind forces experienced at each ring, for example, as a result of elevation and/or localised wind gusts and/or turbulence.

The delay or time lag may increase with increasing distance between rings.

Consequently, there may be a large difference between the top of the apparatus and the ground station, i.e. the revolutions per minute and/or torque of the uppermost rings nearest the lift device, may not equal the revolutions per minute and/or torque of the lower most rings nearest the ground station.

The difference in rotation speed and/or torque between adjacent rings may cause the apparatus and/or lines to twist.

The twist may orient the lines in a helical configuration.

The lower the stiffness in the apparatus, e.g. the lines and/or rings, the greater the time lag may become.

The greater the stiffness in the apparatus, e.g. the lines and/or rings, the lower the time lag may become.

An apparatus, e.g. lines and/or rings, with a greater stiffness may transfer torque more efficiently, and/or more quickly, than an apparatus, e.g. lines with a lesser stiffness.

The stiffness of the lines and/or rings may be variable.

The size, e.g. diameter, of the rings and/or the length of the lines may be variable. The rings may be expandable and/or collapsible, for example, may be telescopic. The rings may expand radially outwardly, i.e. to increase radius and circumference.

The ring may be circular in cross section, i.e. may be toroid in shape. The ring may comprise a void disposed within the circular cross section, i.e. in the interior of the torus.

The ring may be tubular.

The ring may be hollow.

The ring may comprise an aerofoil cross section.

The ring may comprise a tensile line disposed inside the ring, for example, running centrally within the interior of the torus and/or tube.

The ring may comprise, or be formed of a plurality of discrete ring sections.

The ends of the discrete sections may be shaped to allow interconnection and/or docking of the discrete sections.

The tensile line disposed within the ring may be adjustable and/or may be reeled in and/or out allowing adjustment of the circumference of the ring and/or discrete ring sections of the ring. For example, the discrete ring sections may be separated and/or disconnected.

The tensile line may form a tensile ring.

Advantageously, the ring may take the form of two configurations, a first rigid configuration in which the discrete sections are connected to form a rigid ring of a first diameter. The tensile line disposed within the ring may then be expanded and the tension on the discrete sections may be removed, allowing the discrete sections to be separated. The ring may then expand to a second larger diameter formed of the tensile line, with a rigidity less than, but diameter greater than that of the first configuration.

The lines may be disposed on an extendable and/or retractable reel, allowing the length of the line to be varied.

The stiffness and/or size of the rings and/or length of the lines may be variable between a first configuration and a second configuration, which may be changed when the apparatus is live, e.g. airborne.

The apparatus may be launched with the stiffness and/or size of the rings and/or length of the lines in a first configuration. The stiffness and/or size of the rings and/or length of the lines may be moved to a second configuration whilst live, e.g. airborne.

The apparatus may be moved between the first configuration and second configuration with active control. Alternatively, the apparatus may be moved between the first configuration and second configuration with passive control.

The apparatus may be moved between the first configuration and second configuration in response to an operator input and/or control.

The rings may have the greatest stiffness when in the collapsed configuration, i.e. the smallest diameter. When the apparatus is acted upon by the wind, tension may be applied to the lines. The rings may have the greatest passive stiffness when in the collapsed configuration, i.e. when not acted upon by the wind.

The lines may have the greatest stiffness when in the retracted configuration, i.e. the shortest length.

Ease of launching may be increased with a stiffer apparatus.

Increase in sweep area, i.e. area covered by the apparatus, may be increased with a larger apparatus. Power take-off and/or power generation may be increased with a larger sweep area. Stiffness may be reduced with a larger apparatus.

Advantageously, the apparatus may be launched while the apparatus is in the collapsed configuration, i.e. shortest lines and/or smallest diameter rings, thereby easing the launch procedure; and once airborne, the apparatus may be extended and/or expanded, i.e. longer lines and/or larger diameter rings, thereby increasing sweep area and power take off and/or power generation.

Thereby, the apparatus may be launched while the apparatus has the greatest stiffness, and once airborne, be extended to provide greatest sweep area.

The apparatus may comprise a ground station.

The ground station may comprise an electrical generator.

The generator which may convert the energy captured from the wind into energy in the form of electrical generation, and/or mechanical, hydraulic drive or the like. The generator may comprise a power wheel, which may be connected to an electrical generator, dynamo or the like. The generator may comprise a mechanical drive arrangement such as a pump, gear box or the like. The generator may comprise a hydraulic drive arrangement such as a hydraulic pump or the like.

The rotor element may be connected to the generator, and/or may be connected to the power wheel. The rotor element may be connected to the generator and/or power wheel by the driver lines. Thereby, rotation of the rotor element may cause rotation of the power wheel, thereby causing rotation of the generator. Alternatively, the generator may not comprise a power wheel, and the rotor element may connect directly to the electrical generator and/or dynamo, and/or mechanical drive arrangement and/or hydraulic drive arrangement.

Alternatively or additionally, the apparatus may be used in reverse, for example, the generator may be actively driven, by, for example a motor, thereby driving rotation of the autogyro. Driving the autogyro may generate and/or increase line tension, pressure field enhancement, lift power or the like and/or to deliberately agitate air and/or generate air turbulence.

The apparatus may provide power to the generator through rotation of the energy capture device. By such provision, when in use the energy capture device may provide continuous output of power.

The generator system may be located on the ground, by such provision, no large and/or heavy components of the generator need to be suspended and/or be airborne. By such provision, all heavy components may be located on the ground, increasing safety and ease of use of the device and/or required airborne mass may be minimised.

Alternatively the generator system may be located on a surface of water, for example, may be floated on the surface of water, and/or may be disposed on a floating platform. The generator system may be located on and/or connected to a base. The base and/or platform may be configured for automatic adjustment, for example, tilting, in response to and to counteract an applied load. The platform and/or base may be or take the form of a truncated cone. The platform and/or base may comprise an anchor which may be configured to resist torque and/or forces applied upon it by the apparatus.

The ground station may comprise an anchor which may be configured to securely and safely connect the apparatus to the ground.

The apparatus may contact the ground at a single point. By such provision, the ground area is minimised and thus the power generation per unit area is increased.

The apparatus may contact the ground at a plurality of points and/or areas.

The anchor may comprise a single point contact with the ground and/or water.

The anchor may comprise a plurality of contact points with the ground and/or water The anchor may comprise an anchor arrangement.

The anchor arrangement may comprise a plurality of anchors. The plurality of anchors may be arranged in a circular array. Alternatively or additionally, the plurality of anchors may be arranged in a polygonal and/or linear array. The anchors may be disposed underground and/or may be supported and/or restrained by a foundation structure or support, such as concrete, steel reinforcing bars or the like.

The anchor arrangement may comprise a supporting ring, which may be configured to support and/or connect to the power wheel. The power wheel may be connected to the supporting ring by a bearing or similar friction reducing device. Alternatively or additionally, the power wheel may be connected to the supporting ring via a moveable rail. Alternatively or additionally the power wheel may be connected to the supporting ring via a trolley device. The trolley device may be connected to the supporting ring via a bearing or other suitable friction reducing device, a wheel, a track or the like. The power wheel may be disposed concentrically and radially inwardly from the supporting ring. Alternatively, the power wheel may be disposed concentrically and radially outwardly from the supporting ring. Alternatively, the power wheel may be concentric with the power ring and may be axially offset from the power ring.

The supporting ring may be connected to the anchors and may be configured to be stationary or substantially stationary relative to the power wheel. The power wheel may be configured to rotate relative to the supporting ring.

The supporting ring may be connected to each anchor by a plurality of anchor tethers. The anchor and tethers may apply a restraining force on the supporting ring, thereby supporting the tensile forces exerted on the apparatus and the anchor arrangement by the energy capture device and/or lift device.

In a preferred embodiment, each anchor will connect to the supporting ring by three anchor tethers. The anchor tethers may be angled relative to the plane of the supporting ring, thereby providing an oblique restraining force. By such provision, the anchor tethers may support and/or restrain the supporting ring in a plurality of directions. In use, the tensile forces acting on the supporting ring exerted by the apparatus, and the restraining forces exerted by the anchor tethers may be equal or substantially equal. The forces may be isotropic, i.e. the supporting ring may be in a steady state and may be substantially stationary.

The plurality of anchor lines emanating from each anchor may connect to the supporting ring at different locations on the supporting ring, which may be on opposing sides of the supporting ring, for example, each tether may be offset by 120°.

The lengths of each tether may be adjustable.

The length of each tether may be fixed.

In the case where each tether length is fixed, the supporting ring may be able to rotate. The anchor arrangement may comprise a rail system which may be disposed on the ground. The tethers may be connected to one or more trolley which may be connected or attached to the rail system. The trolley may be configured to move along the rail system. The fixed length tethers may be moved on, and supported by the rail system. In this way, passive realignment of the apparatus and/or the supporting ring to align with the wind is permitted.

The rail system may comprise, be, or form a tensile ring and/or a net which may be set inside a plurality of anchors.

The anchor arrangement may be configured to move and/or reposition in the wind.

The anchor arrangement may be configured to move and/or reposition in the wind in a passive manner. The anchor arrangement may be configured to track changes in the wind direction. In this way, the apparatus and/or anchor arrangement may act as a weather vane and automatically position itself downwind of the prevailing wind.

The anchor arrangement may be actively driven to move and/or reposition in the wind. The anchor arrangement may be actively driven on the rail system. The anchor arrangement may be actively driven using, for example a motor and/or traction arrangement, The anchor may apply a restraining force on the tethers.

The tethers may be supported by the anchor.

The tethers may be free to move relative to the anchor, for example, the tether may pass through a connection arrangement.

The connection arrangement may comprise, for example, an eye-bolt, pulley, sheave or the like. The connection arrangement may be connected to the anchor. In this way, a restraining force may be applied to the tether, whilst still permitting movement of the tether relative to the connection arrangement.

The anchor arrangement and/or anchor tethers may be configured such that the relative lengths of each tether may be variable. The length of a portion of the tether between the supporting ring and the connection arrangement may be variable.

The position of the supporting ring may be variable.

The position of the supporting ring may be variable as a result of the relative lengths of the portions of the tether between the supporting ring and the connection arrangement.

For example, a first end of the tether may connect to a first side of the supporting ring, pass through the connection arrangement of the anchor, and a second end of the tether may connect to a diametrically opposite second side of the supporting ring. This may be repeated for each anchor and each anchor tether. By such provision if the lengths of a portion of the tether between a first side of the supporting ring and the connection arrangement are shorter relative to the lengths of the portion of the tether between a diametrically opposite second side of the supporting ring and the connection arrangement, the anchor arrangement and/or supporting ring may be angled towards the first side. In order to reposition the anchor arrangement, the relative lengths of the tethers may be varied, for example, the lengths of portion of the tether between the first side of the supporting ring and the connection arrangement may be increased, thereby simultaneously reducing the lengths of the portion of the tether between the second side of the supporting ring and the connection arrangement.

Alternatively or additionally, each anchor tether may be connected to a reel, winch, motor or the like. The length of each anchor tether may be actively controlled by the reel, winch, motor or the like, i.e. the tethers may be reeled in and/or out, thereby adjusting the relative lengths of each tether.

In this way, the position, roll, and pitch of the supporting ring may be adjustable, thereby allowing the anchor arrangement to be adjusted to account for varying wind directions.

The lengths of the tethers may be passively adjustable, i.e. in response to the wind. Alternatively or additionally, the lengths of the tethers may be actively adjustable, i.e. may be motored, powered or the like. Alternatively or additionally, the lengths of the tethers may be manually adjustable.

The generator may be connected or attached to the supporting ring, which may attach to the circumference of the supporting ring.

The position of the generator on the supporting ring may be adjustable. The position of the generator on the supporting ring may be passively or actively adjustable, for example, the generator may be free to rotate on the supporting ring, thereby passively repositioning itself under gravity to the lowest point on the supporting ring. Alternatively or additionally, the generator may be actively driven along the circumference of the supporting ring, using for example, a motor and traction device.

The generator may be supported by the supporting ring. The generator may be driven by the power wheel, permitting the generation of power. The generator may apply a resistance to the power wheel, in order to generate power, e.g. acting as a dynamo or the like.

The anchor arrangement may comprise an anchor point for the lift line. The lift line anchor may be a single point anchor, which may be disposed centrally within the anchor arrangement. The lift line anchor may be positioned on the ground. The lift line may pass through the centre of the supporting ring, i.e. axially centrally. Alternatively or additionally, the lift line may connect to one or more of the anchors of the anchor arrangement.

The ground station may comprise one or more sensor, which may be configured to measure one or more of azimuth, altitude, elevation, position, line angles, passive tracking form for ease of maintenance, strain and/or tension in frames, anchors, bearing joints, ground plate, motor, line tensions perpendicular alignment to a power take-off (PTO), plane and gearing or the like, in order to provide a full state analysis of the ground station or apparatus. The temperature of components and consumables such as oil may also be measured using a suitable measurement or sensing arrangement.

Alternatively or additionally, sensing and or performance monitoring may be performed via, for example, pressure field, LIDAR, acoustic monitoring, thermal imaging, strain gauges, rotor speed, wind speed data at varying locations throughout

the wind field and stack positions or the like.

The ground station may be configured to vary the apparatus, or components of the apparatus, for example, kite and/or wing, active power ring, autogyro or stack, as outlined above, in order to vary the behaviour and/or output and/or characteristics of the apparatus and/or system. For example, to vary the capacity of the system, PTO, power generation, track alignment of the axis of rotation, track alignment of the axis of the stack and/or apparatus, to vary, e.g. minimise vibration of the system, reduce wobble of the stack and/or apparatus.

The ground station may be configured to adjust PTO levels to match system capacity.

The ground station may be configured to communicate between components of the apparatus.

The ground station may be configured to vary parameters of the system, in response to measured parameters of the system and/or external parameters.

As described above, the apparatus may comprise a control system.

The control system may be configured to detect a parameter, e.g. a parameter of the apparatus and/or the wind.

The control system may be configured to output data.

The control system may be configured to process said parameter and/or data.

The control system may utilise tension in the system, e.g. tension in the lines, as a measure of power take off (PTO). For example, tension may be used as a proxy for torque and/or torque transmission, and/or torque information.

The control system may be configured to use the data and/or parameter to control the apparatus.

The control system may be configured to use the data and/or parameter for determining a control state of the apparatus and/or level of power generation and/or safe level of power generation.

The control state of the apparatus may comprise one or more of azimuth, altitude, elevation, angle, position, rotational speed, tension or the like of the system, power take off (PTO), power generation, line tension, line angle, torque transfer, stress and strain of the system or the like.

The control system may comprise a data processing means, for example, an on-board computer, microprocessor, Arduino, electronic control circuit or the like.

The control system may comprise a plurality of data processing means. The plurality of data processing means may be configured to communicate with each other, i.e. transfer data and/or signals between each data processing means.

As described above, the apparatus may comprise a sensor arrangement.

The sensor arrangement may comprise one or more sensor.

The sensor arrangement may be configured to measure the one or more parameter of the apparatus and/or the wind and output one or more signal, e.g. data signal, indicative of said parameter.

The sensor arrangement may be configured to measure torque of the apparatus The sensor arrangement may be configured to measure tension throughout the apparatus, for example, in the lines, wings, or kites or the like.

The control system may use tension data as a parameter for providing the current status of the system.

The control system and sensor arrangement may measure and/or monitor current rotational speed, e.g. revolutions per minute (RPM), rotational position, angular velocity or the like of the apparatus. The rotational speed and/or rotational position may be measured at a single position, or may be measured at a plurality of different locations.

The control system and sensor arrangement may measure and/or monitor the magnitude of current power take off (PTO).

The sensor arrangement may measure parameters, for example torque of system, torque transfer along the length of the system, stress and strain or the like.

The control system may be ground based, for example, disposed, located at, within, or adjacent the ground station.

The control system and/or communication system may be independently operable, and/or may independently communicate or coordinate between components, for example, the lifter, the top of the stack, the ground station, the rotor blade, fuselage, kite and/or wing or the like.

Alternatively or additionally, the control system may be disposed in an airborne position, for example, on the rotor element, lift kite, driver lines, lift line or the like.

The airborne control system may be configured to communicate and/or transfer data, for example, tension, rotational speed, PTO data, with the ground based control system.

The airborne control system may measure the number of rotations of the energy capture device in a given time period at an airborne position. The ground based control system may measure the number of rotations of the energy capture device in a given time period at ground based position. The control system and/or ground station may compare the number of rotations measured at an airborne position to the number of rotations measured at a ground based position. Additionally or alternatively, the rotational position may be measured at different positions, for example, at an airborne position and at a ground based position. By such provision, any twist or tangle on the system can be measured. For example, if the number of rotations and/or rotational position measured at an airborne position is equal to the number of rotations and/or rotational position measured at a ground based position, then there is no twist of the system. If the number of rotations and/or rotational position measured at an airborne position is different to the number of rotations and/or rotational position measured at a ground based position, the system is twisted.

The control system may be configured to adjust, reduce, increase, or remove any twist measured in a system, by, for example, controlling the position, bank angle, angle of attack, sweep angle or the like of one or more of the kite and/or wings so as to adjust the speed of rotation of an energy capture device relative to another energy capture device. By such provision, the system can be untwisted as required.

The control systems, e.g. airborne and ground based may be configured to measure azimuth, altitude, angle, position, rotational speed, tension or the like of the system.

The ground based control system may allow a failure to occur in the apparatus or a component of the apparatus, e.g. in the ground station, whilst allowing the airborne control systems to continue unaffected.

The airborne control system may allow a failure to occur in the apparatus or a component of the apparatus, e.g. in the autogyro, whilst allowing the ground based control system to continue unaffected.

The ground based control system, may, in response to data received from the airborne control system, perform a specific control action. The control system may comprise an actuator, for example, electronic, mechanical, hydraulic or pneumatic actuator, for example, motors, reels, switches or the like. For example the reel may be actuated by the control system so reel in or out, a portion of line, thereby varying the tension.

The specific control action may comprise, reposition of autogyro system, adjustment of line tension, for example, driver lines, bridles, lift line or the like. The specific control action may be performed by the actuator.

By such provision, the control system may be configured to be adjusted to provide maximum power generation for given conditions by balancing the measured parameters, for example the PTO, rotational speed, line tension, torque transfer, stress and strain of the system or the like.

Advantageously, the control system may perform the control action as a preemptive or preventative action to avoid the apparatus, for example, the power rings, becoming compressed, deformed or collapsed as a result of torque and forces exerted on the system by the rotation of the system. The control system may control and configure the system to perform optimally for given conditions, such as, rotational speed, power take off and power generation.

The control system may provide the ability to monitor and/or assess how the state of the apparatus relates to the power take off and power generation.

The control system may utilise torque transfer as a measure of power take off (PTO) The tension in the system, and/or imposed on the system may provide a measure of energy output and/or power take out and/or power generation.

Tension in the system, e.g. the lines, may be used to monitor capacity of the transmission system, for example, the amount of power transferred from the capture device to the generator.

The control system may sense, detect or monitor tension within the system.

The control system may sense, detect, or monitor the geometry of the system, for example, the spacing and/or diameter of the rings, rigidity and/or strength of the system.

The control system may utilise information for controlling operation, herein referred to as operation control parameters.

The operation control parameters may include, for example, tension information, and/or geometry and/or strength information or the like.

Tension information may be the primary operation control parameter.

Alternatively or additionally, the control system utilise information for secondary control, herein referred to as supervisory control parameters.

The supervisory control parameters may include, for example, wind speed, apparatus alignment, system health, system status information or the like. The supervisory control parameters may supplement the operation control parameter in order to provide additional status information.

The wind energy capture apparatus may have a high degree of automation, i.e. the apparatus may be designed to fly autonomously with negligible or no flight control input required by an operator. By such provision, safety of operation of the apparatus may be enhanced.

The apparatus may comprise one or more line for controlling one or more components of the wind energy capture apparatus which may be formed, made or manufactured of suitable high strength, low weight connecting means such as, ropes, cables, lines, cord, Dyneema® rope or the like. These lines are hereinafter referred to as control lines.

Winching of the components of the apparatus, for example, the control lines, driver lines, rotor elements may be performed using the lift line.

The position and relative positions of the rotor element, and/or the position of the complete apparatus may be repositioned and/or reconfigured when in use, i.e. when live, in order to perform specific manoeuvres, for example, to achieve maximum power for given wind speed, to provide constant power via repositioning in the wind window, to provide constant power generation via cyclic changes to kite and/or wing and/or rotor element characteristics, e.g. pitch, yaw, roll angles, to provide maximum lift for given wind speed and/or to provide maximum drag to reduce power generation, to pull to one side of the wind window in order to stall, to pull to one side of the wind window with gradual release/dissipation of power generated, to pull to one side of the wind window to stop power generation, to reconfigure the kites and/or wings to reduce power generation, to back-stall individual kite and/or wings to vary and/or reduce power generation, to redistribute forces and centre of mass of the system, to vary the impact the autogyro and/or apparatus has on the wind passing through and/or over the autogyro and/or apparatus, for example, increasing or reducing impact on the wind and/or airflow, to vary the inductance factor of the turbine, to vary PTO and/or power available ratio, to vary agitation efficiency of the airflow or the like. Alternatively or additionally, the apparatus may be reconfigured in order to vary the rigidity and/or tension of the apparatus.

The rotor turbine element will create turbulence and/or wake as it moves through the air when in use. The relative positions of rotor elements may be variable relative to each other, the driver lines, and/or the lift line. By such provision, a tailored arrangement can be achieved to offer a balance of rotor element separation, and therefore, amount of rotor elements which can be installed on a given length of line, and the wake generated by each rotor element. Adjusting the positions of rotor elements may permit expansion along the driver lines and/or the lift line, thereby providing a greater capture area within the wind window.

The apparatus, and/or control of the apparatus may be configured to be fail-safe, for example, if a component of the device fails, the device may be configured such that the kite and/or wing stalls and/or the force exerted by the energy capture device and/or lift generation device is minimised, and the apparatus falls gently to the ground.

Alternatively or additionally, the apparatus may comprise one or more brake line which may be attached to the rotor element and may be configured to maintain a specific tension on the apparatus and/or may be configured to affect the lift and/or thrust generated by the kite and/or wing.

Alternatively or additionally, the apparatus may comprise a quick release safety system which when activated, may be configured to extend the length of the driver lines, such that the length of the driver line increases relative to the brake line. By such provision, the brake line may be activated and the lift and/or thrust generated by the kite and/or wing may reduce, thereby causing the energy capture device to stall and drop from the sky, lowering the apparatus to the ground. The brake lines and/or quick release safety system may be user controlled, and/or may be autonomously controlled and/or may be computer controlled, e.g. in response to the application of a specific load or external parameters e.g. weather or wind conditions.

The apparatus may comprise at least one sensor. The sensor may detect real time properties and/or data of features of the device, for example position in the wind window, direction of motion, speed of rotation, speed of translational motion in wind window, tension in lines, e.g. driver lines, control lines, lift lines, health monitoring of components, current and forecasted weather and/or wind conditions or the like, data from lift and network kite turbine controllers or clearance from local airspace authorities or the like. The sensor may detect position of a wing and/or a rotor element and/or a stack, for example, azimuth, altitude, position, elevation, line angles, tension or the like.

The sensor may sense strain and tension within components of the device, e.g. frame, anchor, bearing joints, motor, gearing or the like, thereby providing a full analysis of the state of the wind energy capture apparatus.

Kite and/or wing formation and/or rotor element formation may be varied and/or reconfigured by control algorithms based on incoming wind data and/or stack performance and/or condition data.

Power generation rate may be variable based on parameters such line tension, air pressure, line acoustic, speed, wind speed, or the like.

The apparatus may be configured to respond to sensed parameters, e.g. line tension and or weather forecast conditions, such that the operation of the apparatus is optimised for specific conditions. For example, the ground station may comprise motors and actuators, and/or winders which may be configured to apply a tensile force on one or more lines of the apparatus so that the tension on said lines can be varied while live, i.e. while the apparatus is flying. For example, the apparatus may be configured to optimise one or more of rigidity of lines or kite and/or wings, distances between tethers, angles between tethers, distances between power rings or the like. Consequently, the apparatus can be modified in a pre-emptive manner to compensate for external forces and/or conditions.

The apparatus may comprise a modular construction, and as such may be scaled up or down depending on the required power output or wind conditions. For example, the apparatus may be scaled up or down by increasing or reducing the number of rotor elements in a stack, in particular, the number of active power rings and/or increasing or reducing the number of kite and/or wings on an active power ring. By such provision, reconfiguration of the device may readily be achieved to suit specific application and/or conditions and/or wind speed. Alternatively or additionally, the apparatus may be scaled to provide smoother power transmission on the system, for example, make the system less susceptible to gusts and/or sudden changes in wind direction, and ensuring a more constant power generation and/or PTO.

The power output of the device may scale linearly with number of active power rings used in the device. Alternatively, the power output of the device may scale with number of active power rings at a rate greater than a linear rate, for example may scale exponentially.

Stacking a plurality of rotor elements in this manner may further increase the power generated per weight of the device, and/or may increase the power generated per unit ground area of the device.

The geometry ratio of stacked rings, e.g. radius or separation length, may be directly related to rigidity of the structure.

The apparatus, e.g. the energy capture device, may comprise at least one fairing, aerofoil or other streamlining device which may be connected or attached to the lines, e.g. driver lines, control lines, brake lines or lift line. For example, the lines connecting the rotor element to the generator (driver lines) may comprise line fairing. Alternatively or additionally, the apparatus components, for example, the lines connecting the rotor element to the generator (driver lines), autogyro, active power ring, passive power ring or the like may be constructed or formed of an aerofoil shaped line and/or aerodynamic line fairing, or line covered or encapsulated by an aerodynamic fairing. By such provision, air resistance and/or drag of the lines may be minimised and/or flow turbulence may be reduced and/or flow efficiency may be increased.

Additionally or alternatively, the fairing, aerofoil or other stream lining device may be configured to exert a lift force and/or thrust force, for example, the lines connecting the rotor element to the generator may comprise aerofoils which are configured to exert a force on the lines which acts radially outwards from the axis of rotation of the device. By such provision, the radially outwardly acting force may counteract a compressive force acting radially inwardly towards the axis of rotation, exerted on the lines by the torque of the device when in use. The line fairings may be in the form of compression sleeves which may encapsulate the line. An aerofoil may be fitted within the compression sleeves, further enhancing the streamlined nature of the fairings. The aerofoil may further act to increase the rigidity of the lines.

The discrete lengths of line between adjacent rings may enhance the stability of the fairings. The wind experienced by each discrete length of line may be constant, or generally constant, and there may be negligible variance in wind experienced between each discrete length of line. Advantageously, this improves the efficiency, and efficacy of the fairings.

The apparatus may be collapsible, i.e. fabric kites may be folded, lines may be coiled, and solid components may be flat packed. By such provision, the apparatus may be portable and/or transportable and/or mobile and/or deploy-ability of the device may be enhanced. The collapsible and/or removable nature of the apparatus may permit the device to be installed or uninstalled as necessary, and/or may limit or obviate any environmental impact and/or local planning restrictions, due to the lack of permanent infrastructure required.

The apparatus may be supported by, connected to or underneath a support frame The support frame may take the form of a net frame.

The net frame may comprise a plurality of interconnecting members.

The net frame may comprise a plurality of nodes. The nodes may form a point at which interconnecting members connect.

The net frame may comprise a lattice structure of interconnecting members and nodes.

A plurality of interconnecting members may connect to a single node. For example, 2, 3, 4, 5, 6, 7, 8 or more interconnecting members may connect to a single mode.

The lattice structure may take the form of a plurality of interconnecting polygons, for example, a hexagonal cell structure.

The net may be supported by at least one lift device.

The at least one lift device may connect to a node of the net, for example, on a first side of the net.

The lift kite may impart lift and/or tension on the net. The lift and/or tension applied to the net by the lift kite may be evenly and/or uniformly redistributed throughout the net, i.e. uniform tension in each interconnecting member.

The net frame may be configured to have constant and/or uniform forces throughout the net.

Every interconnecting member in the net may be under tension.

The magnitude of the force experienced in each interconnecting member may vary and/or be variable.

The tension forces in the net frame may be configured such that the nodal distribution pattern remains constant, for example, the forces in the interconnecting members may all be in tension and may all be of a magnitude that allows the position of each node to remain constant, or substantially constant.

The tension forces on each interconnecting member may be constant, or substantially constant. By such provision, the nodes may be restrained in place. The large area of the net relative to a single apparatus may provide an anchor which may restrain, limit, or prevent nodal position drift.

The size and/or shape, e.g. length and/or diameter of the interconnecting members of the net may be configured to ensure that the same, or substantially the same forces are exerted on each of the interconnecting members of the net.

The net frame may be configured so that all interconnecting members, and/or nodes are in tension. The tensile forces of the net frame may act outwardly from each node The net may be formed of a suitable high strength, low weight connecting means such as, ropes, tether, cables, lines, cord, Dyneema® rope or the like The at least one energy capture device may connect to a node of the net, for example, on a second side of the net, opposite the first side of the net.

The net may be configured to support the apparatus. For example, the apparatus and/or autogyro may hang and/or suspend below the net, i.e. on the second side of the net.

The apparatus and/or autogyro may be suspended from a node of the net The net may be configured to permit rotation of the apparatus and/or autogyro relative to the net. For example, the apparatus and/or autogyro may rotate below the net, i.e. below the node.

The net may be configured to limit, reduce, or prevent lateral movement of the apparatus, i.e. the nodes may be restrained in place. The net may act as a tether for the apparatus.

The restriction on the lateral movement of the apparatus imposed by the net may allow multiple apparatus and/or autogyros to be suspended adjacent each other without touching, contacting, or becoming tangled and/or twisted with each other.

The net therefore permits the use of multiple apparatus and/or autogyros which are suspended below the net in an aerial wind farm.

The lightweight nature of the materials and the minimal ground contact area required by a single apparatus allows an aerial wind farm to be scaled up or down with minimal impact.

The net may be used as a framework for the deployment of kite power systems.

The net may be lifted and/or launched by the lift kites, thereby simultaneously lifting and/or launching any apparatus connected to the net.

The lattice structure of the net may form an internal volume.

The net may be used as a means or moving and/or transporting items.

The net may be used as a means of lifting and/or supporting cables, pipes, wires or the like.

The net may support all electrical cabling required for an apparatus and/or for the aerial wind farm.

The net may be connected, attached, anchored to the ground using a tether. The tether may be formed of a suitable high strength, low weight connecting means such as, ropes, tether, cables, lines, cord, Dyneema® rope or the like.

The even and uniform force distribution of the net may allow the apparatus to operate in wind from any direction. For example, the support structure which suspends the apparatus may allow the apparatus to stay suspended in a set position in any direction of wind, by such provision, sudden changes in the wind direction and/or strength, can be tolerated.

The aerial wind farm may be used in an offshore application.

The aerial wind farm may be used at an elevated position.

The lightweight nature of the components of the aerial wind farm may allow the aerial wind farm to be transportable and/or removable.

The collapsible and/or removable nature of the aerial wind farm may permit the aerial wind farm to be installed or uninstalled as necessary, and/or may limit or obviate any environmental impact and/or local planning restrictions, due to the lack of permanent infrastructure required.

The aerial wind farm may be tethered to existing infrastructure, for example, a conventional wind farm, bridge or the like.

The aerial wind farm may be used in combination with, adjacent or above existing infrastructure, for example, a conventional wind farm. Advantageously, the aerial wind farm may use existing infrastructure, for example, electrical grid, offshore cabling, electrical cabling, foundations, transport links or the like, without the need to establish new infrastructure.

The aerial windfarm may allow the wind capture area to be maximised relative to the quantity of materials used, i.e. the aerial wind farm may cover a large area whilst minimising materials used.

The apparatus may be designed with part redundancy. For example, the apparatus may comprise a plurality of rotor elements such that if a single device fails, the remaining rotor elements may continue to operate. Additionally or alternatively, the device may comprise a plurality of driver lines, lift lines and control lines such that if a single line breaks, the device may continue to operate. By such provision, the apparatus may be configured such that if a component of the device fails, the apparatus may remain in use, or may be controllably depowered and lowered to the ground such that a repair or replacement operation may be performed.

The apparatus may be configured such that the apparatus only maintains a rigid structure when under tension. By such provision, if the tension is removed from the system, the system is no longer rigid, thereby, increasing the safety of the system in the event of a failure.

The apparatus may be used in an offshore and/or underwater environment. For example, the apparatus may be mounted to an offshore generation platform or fish farm. Alternatively or additionally, the apparatus may be mounded and/or anchored below the surface of the water. The apparatus may be used as a mixed hydro and airborne systems in which a portion of the apparatus, for example one or more power rings are located below the surface of the water, and a portion, for example, one or more power rings are located above the surface of the water.

According to a second aspect, there is provided a wind energy capture system comprising; one or more the wind energy capture apparatus of the first aspect and a support structure.

The wind energy capture apparatus of the first aspect is hereinafter referred to as an autogyro cell.

The wind energy capture system may comprise a plurality of autogyro cells.

The plurality of autogyro cells may be configured in a network.

The network may be, form, or comprise a lattice formation which may allow autogyro cells to be added in a modular manner. The autogyro cells may be added in stacked formations and/or may be arrayed and/or arranged over ground areas in network cellular patterns such as hexagonal cells.

The network may be formed of, or may comprise a plurality of autogyro cells.

The network system may comprise, or form a wind farm.

The wind energy capture system, i.e. a network of autogyro cells, may occupy less land, and use less material to harness, capture, or generate wind energy than existing AWE systems and conventional wind turbines. Consequently, a network of wind energy capture apparatus may provide significantly improved efficiency.

Repairs to the system and/or network may be simplified when compared to existing systems as the modular autogyro cells may be detached and/or replaced as a single unit, and may be performed on routine schedule or as needed. The network cells may be detached and/or replaced whilst landed or airborne and in use. This provides significant efficiency, ergonomic, and operation benefits.

Kite power capacity factor is maximised by separating lifting kite functions from generating kite functions. Lifting kites can maintain operation through lower wind speeds when their rotors are lowered to the ground station.

In a networked arrangement comprising a plurality of autogyro cells, each device may comprise a lift line. By such provision, individual autogyro cells may be repositionable within the network.

A third aspect relates to use of the apparatus of the first aspect or system of the second aspect to generate electricity and/or drive.

The scale and/or number and/or size of the autogyro and/or active power ring, and/or stack, and/or apparatus may be variable as described above to vary or adjust, e.g. increase or decrease, or maintain constant, the capacity of the system, for example, PTO, power generation or the like.

The apparatus and/or system may be configured to vary the apparatus, or components of the apparatus, by for example, the ground station and/or sensors, in order to, for example, vary the characteristics or form of the kite and/or wing, active power ring, autogyro, stack, as outlined above, in order to vary the behaviour and/or output and/or characteristics of the apparatus and/or system. For example, to vary the capacity of the system, PTO, power generation, track alignment of the axis of rotation, track alignment of the axis of the stack and/or apparatus, to vary, e.g. minimise vibration of the system, reduce wobble of the stack and/or apparatus.

The apparatus and/or system may be configured to adjust PTO levels to match system capacity.

The apparatus and/or system may be configured to communicate between components of the apparatus.

The apparatus and/or system may be configured to vary parameters of the system, in response to measured parameters of the system and/or external parameters.

The invention is defined by the appended claims. However, for the purposes of the present disclosure it should be understood that the features defined above or described below may be utilised, either alone or in combination with any other defined feature, in any other aspect or embodiment or to form a further aspect or embodiment.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other aspects will now be described, by way of example only, with reference to the accompanying drawings, in which: Figure 1 shows a perspective view of the wind energy capture apparatus when the energy capture device comprises a rigid wing; Figure 2 shows a perspective view of the wind energy capture apparatus of Figure 1; Figure 3 shows an enlarged view of the example in Figure 1 to 2 showing the supporting means of the energy capture device on the lift line; Figure 4 shows a perspective view of the rigid wing of Figure 1; Figure 5 shows a perspective view of the wind energy capture apparatus when the energy capture device comprises a non-rigid kite; Figure 6 shows an alternative view of the wind energy capture apparatus of Figure 5; Figure 7 shows an enlarged view of the example in Figure 5 and 6 showing the supporting means of the energy capture device on the lift line; Figure 8 shows a perspective view of the lift kite of the apparatus; Figure 9 shows a perspective view of an energy capture device; Figure 10 shows a perspective view of a stack of a plurality of the energy capture devices of Figure 9; Figure 11 shows the system of Figure 6 while in use; Figure 12 shows a network comprising a plurality of energy capture apparatus supported by a net structure; Figure 13 shows an alternative view of the network of Figure 12; Figure 14 shows an alternative view of the network of Figure 12; Figure 15 shows an example of the network of energy capture apparatus of Figure 12 installed in an offshore wind farm environment; Figure 16(a) to 16(c) show a stacked arrangement of energy capture device in a concentric arrangement; Figure 17(a) to 17(c) show examples of different configurations of the active power rings and shape of the apparatus; Figure 18 shows an example of different configurations of the active power rings and shape of the apparatus; Figure 19 shows analytical results of the relationship between shaft geometry ratio and compression; Figure 20 shows an alternative example of an active power ring comprising a plurality of fuselages.

Figure 21(a) to 21(c) show an example of an anchor arrangement.

Figure 22(a) to 22(c) show an example of the anchor arrangement in a repositioned configuration.

DETAILED DESCRIPTION OF THE DRAWINGS

Referring first to Figures 1 and 2 of the accompanying drawings, there is shown a wind energy capture apparatus 1 for use in capturing energy from the wind W for use in electricity generation. As shown in Figures 1 and 2, the apparatus 1 takes the form of an airborne wind energy capture apparatus comprising an energy capture device, generally denoted 2, and a lift generation device, generally denoted 3. The energy capture device 2 is configured to capture kinetic energy from the wind W and the lift generation device 3 is configured to apply a tensile force on the energy capture device 2.

The energy capture device 2 comprises a ring 4 (referred to below as the "active power ring") having a plurality of wings 5 extending outwards from and circumferentially spaced around the active power ring 4. In the illustrated apparatus 1, the energy capture device 2 comprises two active power rings 4. The wings 5 are configured to cause rotation of the energy capture device 2.

As shown in Figures 1 and 2, the lift generation device 3 takes the form of a lift kite 6 which is connected to a ground station 7 via bridle 8 and lift line 9. In use, the lift generation device 3 applies tension to the apparatus against an anchor 7a (shown in Figure 2) located at the ground station 7, via the lift line 9. A backline 7b connects the lift line 9 to the anchor 7a, thereby providing a safety tether to prevent the apparatus 1, or a component of the apparatus from detaching from the anchor 7a in the event of a breakaway. While the backline 7b is only shown in Figure 2, it will be understood that a backline may be used in any embodiment of the invention.

Interposed between the energy capture device 2 and the ground station 7 is a transmission system, generally denoted 10, including are a number of rings 11 (referred to below as "passive power rings"). Each of the passive power rings 11 are connected to the ground station 7 via lines 12. As such, the passive power rings 11 are interconnected, and also connected to the energy capture device 2.

In use, the passive power rings 11 assist in the transfer or torque resulting from rotation of the energy capture device 2 about the lift line 9, and minimise or at least reduce the risk of the apparatus 1 becoming twisted or distorted.

Referring now also to Figure 3 of the accompanying drawings, the lift line 9 is disposed generally on the axis of rotation of the energy capture device 2, such that in use the energy capture device rotates about the lift line 9. As shown in Figure 3, the energy capture device 2 further comprises a supporting arrangement comprising spokes 13 and a bearing 14 The bearing 14 is generally annular in shape and is disposed on the lift line 9, i.e. the lift line 9 is located through the central orifice of the annulus of the bearing 14. The spokes 13 connect the active power ring 4 to the bearing 14. By such provision, the energy capture device 2 is supported by, and free to rotate about the lift line 9.

Referring now also to Figure 4 there is shown an enlarged view of a wing 5 of the energy capture device 2 shown in Figures 1 to 3. The wing 5 takes the form of an aerofoil, clearly visible at the wing tip 15. The wing 5 comprises a leading edge 16 and a trailing edge 17.

The wing 5 is formed of two wing sections 5a, 5b which are connected to, and supported by a fuselage 18. The wing 5 is asymmetric with the lengths of each wing section 5a and 5b being different, with a ratio of wing section lengths of 60:40, i.e. a first section 5a being approximately 60% of the full length of the wing 5, and a second section 5b being approximately 40% of the full length of the wing 5. However, it will be understood that different proportions and ratios of wing section lengths may be used, for example, 50:50, where both sections 5a and 5b are the same length, 70:30, 80:20, 90:10 or the like.

The fuselage 18 comprises two aerofoil shaped sockets disposed on either side of the fuselage which are configured to receive the wing sections 5a, 5b so that the wing sections 5a, 5b can be inserted into the fuselage 18. The wing sections 5a, 5b are secured to the fuselage using a suitable securing means.

The fuselage 18 connects to the active power ring 4 via the bridles 8 (shown in Figure 4). The fuselage provides rigidity to the wing 5 and supports and distributes the loads exerted on the wing 5 by the bridles 8.

It will be understood that the apparatus may take a variety of different forms. For example, and referring now to Figures 5 to 7 of the accompanying drawings, there is shown an alternative wind energy capture apparatus 101 to that shown in Figures 1 to 4.

The apparatus 101 is similar to the apparatus 1 and like components are represented by like reference signs incremented by 100. However, whereas the energy capture device 2 of the apparatus 1 comprises a number of wings 5, in the apparatus 101 the energy capture device 102 comprises a number of non-rigid kites 105.

As shown in Figures 5 and 6, the apparatus 101 takes the form of an airborne wind energy capture apparatus comprising an energy capture device, generally denoted 102, and a lift generation device, generally denoted 103. The energy capture device 103 is configured to capture kinetic energy from the wind W and the lift generation device 103 is configured to apply a tensile force on the energy capture device 102.

The energy capture device 102 comprises a ring 104 (referred to below as the "active power ring") having a plurality of wings 105 extending outwards from and circumferentially spaced around the active power ring 104. The energy capture device 102 comprises three active power rings 104. The wings 105 are configured to cause rotation of the energy capture device 102.

In Figure 5, the kites 105 corresponding to specific active power rings 104 are shaded for clarity.

As shown in Figures 5 and 6, the lift generation device 103 takes the form of a lift kite 106 which is connected to a ground station 107 via bridle 108 and lift line 109. In use, the lift generation device 103 applies tension to the apparatus against an anchor 7a (shown in Figure 2) located at the ground station 107, via the lift line 109.

Interposed between the energy capture device 102 and the ground station 107 is a transmission system, generally denoted 110, including are a number of rings 111 (referred to below as "passive power rings"). Each of the passive power rings 111 are connected to the ground station 107 via lines 112. As such, the passive power rings 111 are interconnected, and also connected to the energy capture device 102.

In use, the passive power rings 111 assist in the transfer or torque resulting from rotation of the energy capture device 102 about the lift line 109, and minimise or at least reduce the risk of the apparatus 101 becoming twisted or distorted (shown in Figure 11).

Referring now also to Figure 7 of the accompanying drawings, the lift line 109 is disposed generally on the axis of rotation of the energy capture device 102, such that in use the energy capture device rotates about the lift line 109. As shown in Figure 7, the energy capture device 102 further comprises a supporting arrangement comprising spokes 113 and a bearing 114. The bearing 114 is generally annular in shape and is disposed on the lift line 109, i.e. the lift line 109 is located through the central orifice of the annulus of the bearing 114. The spokes 113 connect the active power ring 104 to the bearing 114. By such provision, the energy capture device 102 is supported by, and free to rotate about the lift line 109.

Figure 8 shows an enlarged view of the lift kite 106 of the wind energy capture apparatus 101. The lift kite 106 is designed to provide lift when exposed to wind W. When the lift kite 106 is subjected to the wind W, the lift kite occupies a designed aerodynamic shape and profile. In this example, the lift kite 106 takes a generally parabolic shape, e.g. parachute shape.

The lift kite 106 is of the form of a conventional kite suitable for proving lift, which in this example is a sled kite. However, other such kite designs may be utilised without affecting the function of the lift kite. Other such examples may include a ram air kite, foil kite, leading edge inflatable (LEI) kite, box kite, rigid frame kite or the like. The lift kite 106 is connected to the lift line 109 via a bridle 108. The bridle 108 comprises a plurality of lines which connect the wing tips and the canopy of the lift kite 106 to the lift line 109, and are designed to ensure that the lift kite 106 maintains its designed shape to achieve maximum lift. The bridle 108 also ensures even tension is applied to the lift kite 106.

Figure 9 shows an enlarged view of the energy capture device 102. The energy capture device 102 comprises an active power ring 104, which forms a substantially circular hoop. The active power ring forms an annular aerofoil, i.e. it tapers to form a converging nozzle when viewed from the ground station side (i.e. underside). By such provision, the active power ring may provide thrust and/or lift, and may alter the aerodynamic performance of the energy capture device, e.g. it may provide lift to the energy capture device.

Circumferentially disposed on the active power ring 104 are three non-rigid kites 105. The kites 105 each comprise bridles which allow the kites to be connected to the driver lines or an additional energy capture device 102 or passive power ring 111 (shown in Figure 10).

The kites 105 generate a lift force 32 which acts generally longitudinally along the length of the driver lines 112, a propulsion force 34 which acts generally tangentially to the active power ring 104, and an expansion force 36, which acts generally radially outwards from the active power ring and acts to longitudinally expand the kites 105. These forces provide a resultant force 30 which acts generally upwardly (i.e. away from the ground station) and radially outwardly from the active power ring 104 Figure 10 shows a plurality of the energy capture devices 102 arranged into a stack 40. Each of the energy capture devices 102 is connected to an adjacent energy capture device 102.

Referring first to the upper most energy capture device (i.e. the energy capture device longitudinally farthest away from the ground station and shown at the far right of Figure 10), the energy capture device 102 comprises the active power ring 104 to which the kite 105 is circumferentially attached, connected or disposed. The kite 105 comprises bridles 108 which connect the kite 105 to the active power ring 104 of the adjacent energy capture device 102. Each energy capture device 102 is also connected to the driver line 112 at the circumference of the active power ring 104. By such provision, each energy capture device 102 is connected to an adjacent energy capture device 102 by the driver lines 112. In this example, the stack 40 comprises four energy capture devices. Each energy capture device provides a lift force 32, a propulsion force 34 and an expansion force 36. Each of these forces are transferred to the adjacent energy capture device 102. Beneficially, each energy capture device 102 provides a propulsive force to the apparatus, providing a resultant propulsive force 34a for the complete stack 40, causing the stack 40 to rotate about the central axis A. Referring now to Figure 11, there is shown the apparatus of Figure 6 which, while in use the lines 112 have become twisted due to the torque applied upon the system. The wings of the energy capture device have been removed and lift line 109 has been shown as a dashed line to aid clarity.

As in Figures 5 and 6 above, the wings (not shown) cause the capture device 102 to rotate about the lift line 109. The direction of rotation is denoted R. However, as the structure is not rigid and adjacent rings are only connected by non-rigid lines 112, when the capture device 102 rotates the lines 112 move relative to the adjacent rings.

The rings will rotate at different speeds until the tension forces within the lines equalise, i.e. each ring will rotate at the same speed, or substantially the same speed when in a stead state condition, e.g. at constant rotational velocity, however, when in a non-steady state, e.g. accelerating or decelerating the tension forces will not be equal and thus each ring will rotate at different speeds. Consequently, adjacent rings rotating at different speeds introduces a time delay or lag.

This lag is increased over larger distances, and so there can be a large difference between the top of the apparatus 101 and the ground station, i.e. the revolutions per minute of the uppermost rings is not equal to the revolutions per minute of the lower most rings nearest the ground station. This difference in rotation between adjacent rings can introduce twist into the apparatus 101 and the lines 112 become oriented at an oblique angle to ring 104, thereby creating a helical configuration.

Although Figure 5 and 6 comprise a plurality of kites rather than rigid wings, it will be understood that an apparatus comprising rigid wings as shown in Figure 1 and 2 will also become twisted in a similar manner as shown in Figure 11.

Figures 12 to 14 show an aerial wind farm 201 in which the net, generally denoted 202 comprises a plurality of interconnecting members 203 and nodes 204. Three interconnecting members 203 are connected to each node 204, thereby creating a hexagonal lattice structure 205. The net 202 is configured such that all interconnecting members 203 are under constant tension, and as such. each node 204 is restrained in position. A lift kite 6, 106 is connected to each node. The lift kite 6, 106 applies lift and tension to the nodes 204, thereby supporting the net 202. The lattice structure 205 of the net 202 passively redistribute the tensile forces applied to the net 202 by the lift kite 6, 106, such that the tension in each interconnecting member 203 is uniform or substantially uniform. Apparatus 1, 101, is suspended below each node 204, and is supported by the net 202 and the tension applied by the lift kite 6, 106. The apparatus 1, 101 is able to rotate around the lift line (not shown) and below the net 202. Anchor tether 207a provides a support for the net 202 and connects the net 202 to the ground G. As shown in Figure 13. any turbulent airflow W' causes the forces 206 exerted on the nodes 204 by the lift kite 6, 106 to act in varying directions. However, the redistribution of tension within the interconnecting members 203 of the net 202 restrain the nodes 204 in position, allowing the apparatus to operate efficiently and without the apparatus 1, 101 become tangled, even in the presence of turbulent air flow W'. The apparatus 1, 101 has been removed from Figure 13 for clarity.

Figure 15 shows an illustration of the aerial wind farm 201 installed above an existing, conventional off-shore wind farm comprising a plurality of wind turbines T, highlighting the size advantages of AWE systems and their ability to cover a large wind window area whilst minimising ground contact area and required infrastructure.

Advantageously, installing an aerial wind farm 201 adjacent a conventional wind farm in this way allows the aerial wind farm 201 to use existing infrastructure such as offshore cabling, pipelines, electricity grid, electrical cabling or the like, and allows the aerial wind farm 201 to be installed quickly and efficiently without the need to install necessary services or infrastructure. Further advantageously, the aerial windfarm 201 allows the wind capture area to be maximised relative to the amount of materials used, i.e. the aerial wind farm 201 can cover a large area whilst minimising materials used.

Figure 16(a) to 16(c) show a configuration of the apparatus comprising a plurality of active power rings 304 of differing diameters arranged in a concentric and coplanar arrangement, i.e. one disposed radially inwardly from another on the same plane. These coplanar and concentric rings 304 define a layer 305. A plurality of layers are disposed longitudinally along the axis of rotation of the apparatus 301. In this example, the apparatus 301 comprises six layers 305, each layer 305 comprising four rings 304 disposed radially inwardly from each other. Consequently, the apparatus 301 comprises twenty four rings 304. Each ring 304 comprises six kites, the resultant forces of the kites in this Figure depicted as arrow 305. As such, apparatus 301 comprises one hundred and forty four kites 305. This arrangement advantageously permits extensive scaling of the apparatus 301 to meet specific requirements, with no increase in ground based area.

Figure 17(a) to 17(c) and Figure 18 show examples of different configurations of the rings 404 and shape of the apparatus 401. A measure of horizontal sweep, denoted 412a, 412b and 412c show a depiction of the quantity of wind captured by the apparatus 401, illustrated as a wind shadow. The larger the area of 412, the greater quantity of wind is captured by the device and the greater the power generated by the device 401. Figure 17(a) to 17(c) illustrates how the capture area varies for different configurations of apparatus 401, including longitudinal length and diameter of rings 404a, 404b, 404c, 404d.

Figure 19 shows the relationship between shaft geometry ratio and compression, where the shaft geometry ratio is defined as the ratio of ring radius to ring separation; and the compression defines the compression exerted on the rings by the torque of the system. This relationship is shown for different configurations of the apparatus, comprising either 5 lines, or 8 lines, and for varying levels of torque.

It can clearly be seen that for increased number of lines, the compression is reduced. For example, the 8 line system has reduced compression relative to the 5 line system. Further, as torque is increased, the compression increases.

The maximum compression amount further varies with increasing shaft geometry ratio. For larger shaft geometry ratios, the compression amount reduces, i.e. the less the diameter of the shaft, the greater the compression is for the same tension imposed on the system, whereas the larger diameter shaft has less compression for the same tension. Tension imposed on the system provides a measure of energy output.

These results show valuable information on how the performance of the apparatus varies depending upon certain parameters and configurations, which aids the ability to control the apparatus for specific conditions.

Figure 20 shows an alternative example of the apparatus in Figures 1 and 2, in which, the wings 505 are connected to a fuselage 506. The fuselage 506 is connected to active power ring 504. However, it will be understood that the wings 505 may alternatively connect directly to the active power ring 504 without the need for fuselage 506.

The active power ring 504 is expandable and collapsible, permitting the apparatus to be launched in a collapsed arrangement, in which the stiffness is greatest and ease of launch is increased. Once airborne, the active power ring 504 is expanded. The active power ring 504 is shown here in an expanded configuration. In the collapsed configuration, the multiple fuselages 506 may be connected in a close packed arrangement, for example, with nose 506a of a fuselage 506 abutting the tail 506b of an adjacent fuselage 506. In an expanded configuration, the active power ring 504 is expanded, i.e. the circumference is increased, thereby increasing the separation of the nose 506a and tail 506b of adjacent fuselages 506. The increased circumference of the expanded configuration increases the swept capture area of the apparatus, i.e. the area through which the apparatus rotates. Increasing the capture area in this way increases the power take off of the apparatus.

Turbines 510 are disposed on the wings 505 and are capable of generating power which is used for on-board control, such as powering sensors, motors, winches or the like, or otherwise controlling the wings 505 or fuselage 506, or for exporting to the rest of the apparatus for control or power generation.

Figure 21(a) to 21(c) show an example of the anchor arrangement 601, which is suitable for use for anchoring the apparatus according to the first aspect, illustrated in Figures 1 to 11; and for anchoring the system according to the second aspect, illustrated in Figures 12 to 15.

The anchor arrangement, generally denoted 601 comprises a plurality of anchors 602, in this example, eight anchors; a supporting ring 603 and a plurality of anchor tethers, generally denoted 604. The supporting ring 603 is connected to the anchors 602 via the anchor tethers 604.

Each anchor 602 is connected to the supporting ring 603 by three anchor tethers 604, in which one of the tethers 604a is oriented normal to the supporting ring 603, while the other two anchor tethers 604b, 604c are oriented at an oblique angle to the supporting ring 603. Advantageously, this applies restraining forces on the supporting ring 603 in a range of directions, thereby limiting any rotational movement of the supporting ring 603. However, it will be understood that any number of anchor tethers 604 may be used, for example, 4, 5, 6 or more anchor tethers, with the ability to resist rotational movement increased with increasing numbers of anchor tethers 604.

Disposed circumferentially inside the supporting ring 603 is a power wheel 605. The power wheel 605 is connected to the supporting ring 603 via a bearing or other suitable friction reducing device, such that the power wheel 605 is moveable about the axis of rotation relative to the supporting ring 603, which is substantially stationary due to the restraining forces applied by the anchor tethers 604. The driver lines 612 (shown in Figure 21(a) only) connect to the power wheel 605 such that rotation of the autogyro (not visible in Figure 21(a) to 21(c)) causes rotation of the power wheel 605, without imparting forces or rotation on the supporting ring 603.

Disposed on a circumferential rim of the supporting ring 603 is a generator 606.

The generator 606 is supported by the supporting ring 603, and makes contact with the power ring 605, such that rotational of the power ring 605 drives the generator 606.

The anchors 602 comprise a connection arrangement 607 (shown in Figure 21a only), to which the anchor tethers 604 are attached. The connection arrangement 607 provides a restraining force for the anchor tethers 604, whilst permitting movement of the anchor tethers 604. The connection arrangement 607 takes the form of an eye-bolt or sheave or the like, such that the anchor tether 604 may pass freely through the connection arrangement 607. This permits the relative lengths of the anchor tethers 604 to be varied to adjust the position and/or angle and/or plane of the anchor arrangement 601 to suit a specific wind IN direction. The lengths of the anchor tethers 604 on a first side of the supporting ring 603 may be increased, whilst simultaneously reducing the lengths of the anchor tethers on a second diametrically opposite side of the supporting ring 603. This allows the plane of the supporting ring 603 to be varied such that it always points downwind of wind W and towards the autogyro.

The generator 606 is moveably attached to the supporting ring 603 such that the generator 606 can be repositioned on the supporting ring 603 when the angle and plane of the supporting ring 603 varies depending on the orientation of the anchor arrangement 601, i.e. the generator 606 can be repositioned to the lowest point on the supporting ring 603.

Figure 22 shows an example of when the anchor arrangement 601 has been repositioned to account for a different direction of wind W. The supporting ring 603 has been repositioned by reducing the lengths of the anchor lines 604 on one side of the supporting ring 603 (left side in Figure 22) whilst simultaneously increasing the lengths of the anchor lines 604 on a diametrically opposite side (right side in Figure 22), thereby allowing the supporting ring 603 to tilt to an orientation pointing downwind of wind W (towards the left in Figure 22). Generator 606 has also been repositioned on the supporting ring 603 to account for the new plane of the supporting ring Figure 23 shows an example of the apparatus 1 according to the first aspect, comprising a plurality of rigid wings 5, connected to and anchored by the anchor arrangement 601.

Figure 24 shows an example of the apparatus 101 according to the first aspect, comprising a plurality of kites 105, connected to and anchored by the anchor arrangement 601.

Figure 25 shows an example of the wind energy capture system 201 according to the second aspect, connected to and anchored by a plurality of the anchor arrangements 601.

It will be understood that various modifications may be made without departing from the scope of the claimed invention.

Claims

CLAIMS1. A wind energy capture apparatus comprising: an energy capture device configured to capture kinetic energy from the wind, wherein the energy capture device is configured to convert the kinetic energy of the wind into rotation of the energy capture device; a lift generation device configured to apply a tensile force to the energy capture device; a transmission system configured to transmit the rotation of the energy capture device to a generator for conversion into electricity or mechanical drive; and a sensor arrangement configured to detect one or more parameters of the apparatus, wherein the apparatus comprises, is coupled to or is operatively associated with a control system operatively associated with the sensor arrangement, the control system configured to receive data output from the sensor arrangement and configured to control the apparatus using said data.
2. The wind energy capture apparatus of claim 1, wherein the control system is configured to read the detected parameter and use said parameter in the control of the apparatus.
3. The wind energy capture apparatus of claim 1 or 2, wherein the sensor arrangement is configured to detect the tension in a component of the apparatus, and the control system is configured to use the tension as a measure for determining a control state of the apparatus and/or level of power generation.
4. The wind energy capture apparatus of any preceding claim, wherein the transmission system comprises a plurality of driver lines which connect the energy capture device to the generator.
5. The wind energy capture apparatus of any preceding claim, wherein the energy capture device comprises one or a plurality of active power rings.
6. The wind energy capture apparatus of claim 5, wherein at least one of: the active power rings are arranged longitudinally along the length of the axis of rotation of the apparatus; and the active power rings are arranged concentrically.
7. The wind energy capture apparatus of any preceding claim, wherein the wind energy capture apparatus is passively repositionable within a wind window in response to changes in wind conditions.
8. The wind energy capture apparatus of any preceding claim, wherein the energy capture device comprises at least one of: a tensioned line comprising an aerodynamic fairing, a kite, and a wing.
9. The wind energy capture apparatus of any preceding claim, wherein the energy capture device is configured to provide propulsion in a particular direction.
10. The wind energy capture apparatus of any preceding claim, wherein the energy capture device comprises a reel, winder or winch, connected to at least one line or component of the apparatus, and configured to adjust the formation of said line or component.
11. The wind energy capture apparatus of any preceding claim, wherein the energy capture device comprises a turbine, configured to generate electricity for powering components of the device, e.g. sensors.
12. The wind energy capture apparatus of any preceding claim, wherein at least one of the energy capture device, the lift generation device and the transmission system comprises a sensor.
13. The wind energy capture apparatus of any preceding claim, wherein the energy capture device forms the lift generation device.
14. The wind energy capture apparatus of any preceding claim, wherein the energy capture device is adjustable between a first configuration of a first diameter, to a second configuration of a second larger diameter.
15. The wind energy capture apparatus of any preceding claim, wherein the rotational speed of the active power rings is adjustable.
16. The wind energy capture apparatus of any preceding claim, wherein the rotational position of the apparatus is detectable, and wherein the apparatus can be reconfigured to adjust the rotational position of the apparatus in response to the detected position.
17. The wind energy capture apparatus of any preceding claim, comprising a ground station located at or near the ground, the ground station comprising the generator.
18. The wind energy capture apparatus of any one of claims 4 to 17, wherein the driver lines comprise a streamlining device configured for at least one of reducing air resistance and generating a radial force towards or away from the axis of rotation of the apparatus.
19. A wind energy capture system comprising; one or more wind energy capture apparatus according to any one of claims 1 to 18; and a support structure.
20. The wind energy capture system of claim 19, wherein the support structure comprises a net, the net comprising a plurality of interconnecting members and nodes, the nodes being the connection point of the interconnecting members.
21. The wind energy capture system of claim 20, wherein the tensile forces experienced in the support structure are distributed across the area of the support structure, such that the position of the node is restrained.
22. The wind energy capture system of claim 19 to 21, wherein the lift generation device is connected a first side of the support structure.
23. The wind energy capture system of claim 19 to 22, wherein a wind energy capture apparatus is connected to a second side of the support structure; and supported by the support structure.
24. The wind energy capture system of claim 19 to 23, wherein the support structure comprises a lattice structure.
25. Use of the apparatus of any one of claims 1 to 18, or the system of any one of claims 19 to 24 to generate electricity.